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2008-22-24: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections of installed low pressure compressor (LPC) fan blade roots on-wing and during overhaul, and relubrication according to accumulated life cycles. Also, that AD introduces application of Metco 58 blade root coating as an optional terminating action. This AD requires the same actions but adds compliance paragraphs to relax the compliance schedule for repetitive inspections for fan blades operating within RB211-535E4 flight profiles A and B, if certain requirements are met. This AD also relaxes the initial compliance threshold by extending the cycles at which an initial inspection is required. This AD results from RR issuing Mandatory Service Bulletin (MSB) No. RB.211-72-C879, Revision 5 and Revision 6, that introduced a relaxed repetitive compliance schedule for fan blades operating within RB211-535E4 flight profiles A and B, if certain requirements are met, and introduced a relaxed initial compliance threshold. We are issuing this AD to detect cracks in LPC fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane.
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87-06-05: 87-06-05 MCDONNELL DOUGLAS: Amendment 39-5572. Applies to McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) series airplanes, certificated in any category, equipped with Aircraft Mechanics, Inc., crew seats model numbers, 1056, 1057, and 1058, having serial numbers 001 through 907 and 911. Compliance required as indicated, unless previously accomplished. \n\n\tTo preclude the potential of damage to crew seat life vests, accomplish the following: \n\n\tA.\tWithin 12 months after the effective date of this AD, inspect the life vest. If any signs of chafing are found, replace before further flight with a serviceable unit. \n\n\tB.\tWithin 12 months after the effective date of this AD, modify the crew seat in accordance with the accomplishment instructions of Aircraft Mechanics, Inc., Service Bulletin 25-DC-10/678-24, dated May 20, 1984, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.C.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles 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 in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-L65 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis Amendment becomes effective April 2, 1987.
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87-18-10: 87-18-10 INTREPRINDEREA DE CONSTRUCTII AERONAUTICE: Amendment 39- 5695. Applies to Model IS-28B2 gliders through serial number 160 inclusive certificated in any category.
Compliance is required as indicated unless already accomplished.
To prevent the failure of the aileron control levers and forks which could result in the glider becoming uncontrollable, accomplish the following:
(a) Within the next 5 hours time-in-service after the effective date of this AD unless compliance with paragraph (c) has been accomplished, visually inspect the aileron control levers P/N 30AD.02.028 and aluminum NIA 181-2 forks using a 10 power or greater magnifying glass for cracks or deformation.
(b) If a cracked or deformed part is found during the inspection required by paragraph (a) of this AD, before further flight, replace the aileron control levers and forks with serviceable levers and forks, new design P/N 30AD.02.028 lever and steel NIA 201-2 fork, in accordance with the accomplishment instructions of Intreprinderea De Constructii Aeronautice Service Bulletin No. IS-28B2-E0-14, dated August 20, 1985. NOTE: The manufacturer has assigned the same part number to the new design aileron lever as the original design aileron lever. The new lever can be identified by measuring the length of the section which is reduced in thickness on the longer arm of the aileron lever. The new design aileron lever is reduced in thickness 42mm from the end of the longer arm whereas the old design aileron lever is reduced in thickness 27mm from the end of the longer arm.
(c) Prior to September 30, 1987, replace any aileron control system levers and forks not replaced in accordance with paragraph (b) of this AD, with serviceable levers and forks, new design P/N 30AD.02.028 lever and steel NIA 201-2 fork, in accordance with Intreprinderea De Constructii Aeronautice Service Bulletin No. IS-28B2-E0-14 dated August 20, 1985. NOTE: The aileron levers removed from service should be destroyed or disfigured to prevent reuse.
Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, Federal Aviation Administration, c/o American Embassy, 15 Rue de la Loi B-1040, Brussels, Belgium; telephone 513.38.30 ext. 2710, or the Manager, Federal Aviation Administration, New England Region, Aircraft Certification Division, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone 516-791-6680.
Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD.
Intreprinderea De Constructii Aeronautice Service Bulletin No. IS-28B2-E0-14, dated August 20, 1985, identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to Sprague Aviation Incorporated, 699 Linwood, Vacaville, California 95688. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, Rules Docket 87-ANE-01 between the hours of 8:00 a.m. and 4:30 p.m.; Monday thru Friday, except federal holidays.
This amendment becomes effective on September 3, 1987.
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89-20-01 R1: 89-20-01 R1 GENERAL ELECTRIC COMPANY: Amendment 39-6337 as revised by Amendment 39-6411.
Applicability: General Electric Company (GE) CF6-6 series turbofan engines installed in McDonnell Douglas DC10-10 aircraft.
Compliance: Required as indicated, unless already accomplished.
To detect the existence of metallurgical imperfections in Stage 1 fan disks which could adversely affect Stage 1 fan disk service life, ultrasonic inspect all Stage 1 fan disks in accordance with the Appendix to this AD, and the following schedule:
(a) All Stage 1 fan disks with those serial numbers listed in TABLE 1 of this AD, immersion ultrasonic inspect no later than October 27, 1989.
(b) All Stage 1 fan disks identified by those serial numbers listed in TABLE 2 of this AD, as follows:
(1) Remove fan rotor spinner cone and contact ultrasonic inspect the installed fan disk no later than November 21, 1989.
(2) Immersion ultrasonic inspect within the next 500 cycles in service after accomplishing the contact ultrasonic inspection requirements of paragraph (b)(1) above, or at the next shop visit after October 7, 1989, or no later than April 1, 1990, whichever comes first.
(c) All Stage 1 fan disks identified by serial numbers listed in TABLE 3 of this AD, as follows:
(1) Remove fan rotor spinner cone and contact ultrasonic inspect the installed fan disk no later than February 4, 1990, and reinspect at intervals not to exceed 500 cycles since the last contact ultrasonic inspection until the immersion ultrasonic requirement of paragraph (c)(2) has been accomplished.
(2) Immersion ultrasonic inspect at the next shop visit after October 7, 1989, but no later than December 31, 1990.
(d) All Stage 1 fan disks identified by those serial numbers listed in TABLE 2A of this AD, as follows:
(1) Remove fan rotor spinner cone and contact ultrasonic inspect the installed fan disk no later than January 23, 1990.
(2) Immersion ultrasonic inspect within the next 500 cycles in service after accomplishing the contact ultrasonic inspection requirements of paragraph (d)(1) above, or at the next shop visit after December 12, 1989, or no later than June 5, 1990, whichever comes first.
(e) All Stage 1 fan disks identified by serial numbers listed in TABLE 3A of this AD, as follows:
(1) Remove fan rotor spinner cone and contact ultrasonic inspect the installed fan disk no later than April 10, 1990, and reinspect at intervals not to exceed 500 cycles since the last contact ultrasonic inspection until the immersion ultrasonic requirement of paragraph (e)(2) has been accomplished.
(2) Immersion ultrasonic inspect at the next shop visit after December 12, 1989, but no later than March 5, 1991.
NOTES: (1) Disks which have been previously immersion ultrasonic inspected in accordance with GE Commercial Engine Memorandum No. 98, Rev. 2, dated October 5, 1989, are considered to be in compliance with the immersion ultrasonic inspection requirements of paragraphs (a), (b), (c), (d), and (e) above.
(2) For the purpose of this AD, "shop visit" is defined as the induction of the engine into the shop for any reason.
(3) Accomplishment of the immersion ultrasonic inspection requirements of paragraphs (b)(2), (c)(2), (d)(2), and (e)(2) above relieves the requirements for contact ultrasonic inspections of paragraphs (b)(1), (c)(1), (d)(1), and (e)(1) above.
(f) Remove from service, prior to further flight, fan disks inspected in accordance with paragraphs (a), (b), (c), (d), and (e) which do not meet the acceptance criteria of the Appendix to this AD and replace with a serviceable part. Report all inspection findings in writing within 10 days of the inspection to the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts, 01803; Telex No. 949301 FAANE BURL.
Information collection requirements contained in this regulation (Section 39.13) have been approved by the Office of Management and Budget under the provisions of the Paperwork Reduction Act of 1980 (Pub. L. 96- 511) and have been assigned OMB Control Number 2120-0056.
(g) 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.
(h) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedules specified in 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.
TABLE 1
MP000382
MP000383
MP000384
MP000386
MP000387
MP000388
TABLE 2
MP000352
MP000363
MP000374
MP000390
MP000407
MP0A0117
MP000354
MP000364
MP000375
MP000393
MP000411
MP0A0133
MP000357
MP000365
MP000376
MP000395
MP0A0108
MP0A0136
MP000358
MP000368
MP000377
MP000397
MP0A0109
MP0A0140
MP000359
MP000370
MP000378
MP000398
MP0A0110
MP0A0141
MP000360
MP000371
MP000379
MP000399
MP0A0111
MP0A0142
MP000361
MP000372
MP000380
MP000402
MP0A0112
MP0A0143
MP000362
MP000373
MP000389
MP000404
MP0A0113
MP0A0145
MP0A0115
TABLE 2A
MP0A0135
MP0A0182
TABLE 3
MP000150
MP000188
MP000222
MP000251
MP000284
MP000319
MP000151
MP000189
MP000223
MP000253
MP000285
MP000320
MP000152
MP000190
MP000224
MP000254
MP000286
MP000321
MP000153
MP000191
MP000225
MP000255
MP000289
MP000322
MP000154
MP000193
MP000226
MP000257
MP000290
MP000323
MP000155
MP000194
MP000228
MP000258
MP000291
MP000325
MP000156
MP000195
MP000229
MP000260
MP000292
MP000326
MP000158
MP000196
MP000230
MP000263
MP000293
MP000331
MP000159
MP000197
MP000231
MP000264
MP000295
MP000334
MP000160
MP000198
MP000232
MP000265
MP000297
MP000336
MP000161
MP000199
MP000233
MP000266
MP000298
MP000337
MP000162
MP000200
MP000234
MP000267
MP000299
MP000338
MP000163
MP000204
MP000235
MP000268
MP000300
MP000339
MP000168
MP000205
MP000236
MP000270
MP000302
MP000340
MP000171
MP000206
MP000237
MP000271
MP000303
MP000341
MP000172
MP000207
MP000238
MP000272
MP000304
MP000342
MP000173
MP000208
MP000240
MP000273
MP000305
MP000343
MP000175
MP000209
MP000241
MP000274
MP000308
MP000346
MP000177
MP000212
MP000243
MP000276
MP000311
MP000348
MP000178
MP000213
MP000244
MP000277
MP000312
MP000349
MP000179
MP000214
MP000245
MP000278
MP000313
MP000350
MP000180
MP000215
MP000246
MP000279
MP000314
MP0A0137
MP000181
MP000216
MP000247
MP000280
MP000315
MP0A0139
MP000182
MP000217
MP000248
MP000281
MP000316
MP0A0207
MP000184
MP000218
MP000249
MP000282
MP000317
MP0A0439
MP000185
MP000219
MP000250
MP000283
MP000318
MP000186
MP000220
MP000187
MP000221
TABLE 3A
MP000618
MP000139
MP000103
MP000011
MP0C2744
MP0A0376
MP000436
MPOOO136
MP000102
MP000010
MP0C0321
MP0A0291
MP000353
MP000113
MP000078
MP000009
MP0A0880
MP0A0284
MP000351
MP000111
MP000016
MP000005
MP0A0810
MP0A0206
MP000294
MP000109
MP000015
MP000004
MP0A0801
MP0A0200
MP000174
MP000108
MP000014
MP000003
MP0A0736
MP0A0139
MP000149
MP000107
MP000013
MP000002
MP0A0662
MP0A0138
MP000141
MP000104
MP000012
MP0H3844
MP0A0481
MP0G2753
The ultrasonic inspections shall be done in accordance with the Appendix to this AD.
This AD revises Amendment 39-6337 (54 FR 38814; September 21, 1989), AD 89-20-01, which became effective on October 7, 1989.
This amendment (39-6411, AD 89-20-01 R1) becomes effective on December 12, 1989.
89-20-01 R1 Appendix
The applicable General Electric Service Bulletin (CF6-6) 72-947, Revision 2, dated November 21, 1989, and the following General Electric Manufacturing and Field Quality Procedures may be obtained from General Electric Company, Technical Publications Department, 1 Neuman Way, Cincinnati, Ohio 45215, or may be examined in the Regional Rules Docket (Docket #89-ANE-35), FAA, New England Region, Office of Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803.
(A) General Electric Manufacturing and Field Quality Technology Procedure No. 391, issued September 15, 1989, Rev. 1, dated September 28, 1989.
(B) General Electric Manufacturing and Field Quality Technology Procedure No. 384, issued September 15, 1989, Rev. 2, dated October 5, 1989.
(C) General Electric Manufacturing and Field Quality Technology Procedure No. 385, issued September 14, 1989, Rev. 2, dated October 5, 1989.
(D) General Electric Manufacturing and Field Quality Technology Procedure No. 389, issued September 14, 1989, Rev. 2, dated October 3, 1989.
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2008-22-02: We are adopting a new airworthiness directive (AD) for Maryland Air Industries, Inc., Model Fairchild F-27 and FH-227 Series Airplanes. This AD requires operators to modify their airplanes and revise their inspection or maintenance programs to incorporate instructions for maintenance and inspection of the fuel tank systems, as appropriate, by December 16, 2008, using information developed in accordance with Special Federal Aviation Regulation 88 (SFAR 88). This AD results from fuel system safety reviews done on similar airplane models in accordance with SFAR 88. These safety reviews identified potential unsafe conditions on Model Fairchild F-27 and FH-227 series airplanes for which the type certificate holder, Maryland Air Industries, Inc., has not conducted SFAR 88 safety reviews, has not provided corrective actions, and does not plan to do so. We are issuing this AD to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
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2000-23-06: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-145 series airplanes, that requires replacement of defective hydraulic tubing in the left and right wings with new hydraulic tubing. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the loss of hydraulic pressure which could result in reduced controllability of the airplane.
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82-15-01 R1: 82-15-01 R1 HUGHES HELICOPTERS: Amendment 39-4414 as amended by Amendment 39-4463. Applies to Model 269A (all S/N's), TH-55A (all S/N's converted to civil use), 269A-1 (all S/N's), 269B (all S/N's), and 269C (S/N's 0001 through 1074) helicopters equipped with main transmission assemblies P/N 269A5175-7, -9, -11, -13, -15, and -17, except those transmissions with the letter "W" on the transmission nameplate below and adjacent to the transmission serial number. Applies to helicopters certificated in all categories.
Compliance is required as indicated unless already accomplished.
To prevent failure of the main transmission, accomplish the following:
(a) Within 50 hours' additional time in service after the effective date of this AD, disassemble the transmission and inspect the ring gear/carrier interface and attachment bolts for possible fretting or cracking, and rework in accordance with Service Information Notice N-181, paragraphs a. through j., or later FAA approvedequivalent. All parts that cannot be reworked within the criteria of Service Information Notice N-181 are considered unairworthy and must be replaced with like serviceable parts.
NOTE: Those portions of Service Information Notice N-181 which address disposition of parts which exceed the prescribed inspection and rework criteria are not applicable.
(b) Reassemble the transmission in accordance with Service Information Notice N- 181, paragraphs k. through o., or FAA approved equivalent.
(c) Special flight permits may be issued in accordance with Sections 21.197 and 21.199 of the Federal Aviation Regulations to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD.
(d) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Certification Field Office, FAA Northwest Mountain Region, 15000 Aviation Boulevard, Room 5W26, Hawthorne, California.
Amendment 39-4414 became effective July 12, 1982.
This Amendment 39-4463 becomes effective October 4, 1982.
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2008-21-02: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 737-600, -700, and -800 series airplanes. That AD currently requires repetitive inspections to detect damage of the aft strut insulation blanket, and eventual replacement of the insulation blankets with new, improved blankets. This new AD adds airplanes to the applicability and requires installation of a new heat insulation blanket and new cover plate on the left and right side engine struts. This new AD does not retain the requirements of the existing AD but does terminate the requirements of the existing AD. This AD results from reports of damaged heat insulation blankets on the engine struts. We are issuing this AD to prevent exposure of the lower surface of the strut to extreme high temperatures, consequent creation of a source of fuel ignition, and increased risk of an uncontrollable fire and possible fuel tank explosion.
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82-24-06 R1: 82-24-06 R1 BRITTEN-NORMAN: Amendment 39-4506 as amended by Amendment 39- 4559. Applies to Models BN-2, BN-2A, BN-2A-6, BN-2A-8, BN-2A-9, BN-2A-26, BN-2A-27, BN2A MKIII, BN2A MKIII-2, and BN2A MKIII-3 (all serial numbers) airplanes certificated in any category.
COMPLIANCE: Required as indicated unless already accomplished.
To prevent possible failure of the carburetor air box shutter, accomplish the following:
(a) Within the next 100 hours time-in-service after the effective date of this AD and at intervals not exceeding 100 hours time-in-service thereafter:
(1) Visually inspect the carburetor air box shutters for cracks or excessive bolt hole wear in accordance with procedures set forth in the "Inspection" section of Pilatus Britten-Norman Limited Service Bulletin Number BN-2/SB.144, Issue: 1, dated July 10, 1980 (hereinafter referred to as the service bulletin).
(A) Prior to further flight, replace any carburetor air box shutter found cracked with newshutter in accordance with "Rectification" section of the service bulletin.
(B) If excessive bolt hole wear is found prior to further flight, modify the shutter in accordance with the "Rectification" section of the service bulletin.
(b) On or before November 1, 1983, replace or modify the air box shutter in accordance with paragraph (a)(1)(A) or (a)(1)(B) of this AD.
(c) The inspection required by paragraph (a) (1) may be discontinued when the modifications or replacements prescribed in paragraphs (a)(1)(A) and (a)(1)(B) of this AD are accomplished.
(d) The airplane may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.
(e) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium.
Amendment 39-4506 became effective on December 2, 1982.
This Amendment 39-4559 becomes effective February 7, 1983.
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2008-20-03: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Fokker Model F.28 Mark 0070 and 0100 airplanes. That AD currently requires a one-time inspection of the main landing gear (MLG) main fitting for cracks, and repair if necessary. The existing AD also currently requires installing a placard and revising the airplane flight manual to include procedures to prohibit the application of brakes during backward movement of the airplane. This new AD requires repetitive eddy current inspections of the MLG main fitting and rework before further flight as applicable. This AD results from reports that a final solution eliminating the cause of the crack initiation mechanism is not yet available and that repetitive inspections are necessary. We are issuing this AD to detect and correct cracks in the MLG main fitting, which could result in reduced structural integrity of the MLG main fitting.
DATES: This AD becomes effective November 3, 2008.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of November 3, 2008.
On April 26, 2006 (71 FR 14363, March 22, 2006), the Director of the Federal Register approved the incorporation by reference of Messier-Dowty Service Bulletin F100-32-106, including Appendices A through C and excluding Appendix D, dated February 18, 2005.
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