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86-19-12: 86-19-12 ALLISON GAS TURBINE DIVISION, GENERAL MOTORS CORP. (Allison, formerly Detroit Diesel Allison): Amendment 39-5373. Applies to Model 250-C30 Series engines installed in, but not limited to, Sikorsky Model S-76A, Bell Models 206L-1, modified to incorporate the Allison 250-C30 engine, and 206L-3, and McDonnell Douglas Helicopter Company (Hughes) Models 369F and 369FF aircraft.
SIKORSKY AIRCRAFT: Applies to Sikorsky Aircraft Model S-76A helicopters certificated in any category and equipped with Allison Model 250-C30 and -C30S engines.
Compliance is required as indicated unless already accomplished.
To prevent conditions that can lead to a possible gas producer turbine rotor uncontained failure and to prevent critical secondary damage in the event of a gas producer turbine rotor uncontained failure, accomplish the following:
NOTE: Paragraphs (a)(1) thru (a)(3) of this AD are equivalent to the technical requirements of AD 84-24- 02 which is superseded by this AD. Paragraphs (a)(4) and (b) delineate final corrective actions for all Model 250- C30 Series engines to prevent the above described failure/secondary damage.
(a) Allison Model 250-C30 and -C30S engines installed in Sikorsky Aircraft Model S-76A helicopters
(1) Within the next 30 days after December 18, 1984, for aircraft in compliance with telegraphic AD (TAD) T84-16-51, and prior to further flight for aircraft not in compliance with TAD T84-16-51, perform the following:
(i) Install the Sikorsky Model A-76A helicopter engine compartment protective shields, P/N 76070-20077-013 or P/N 76070-20077-014, in accordance with Sikorsky Alert Service Bulletin (ASB) 76- 71-7 dated November 9, 1984, or FAA-approved equivalent; and concurrently,
(ii) Install Allison first stage turbine wheel external energy absorbing rings, P/N 23031910, L.H. and 23031920, R.H., around the Allison Model 250-C30 and -C30S engines in accordance with Allison Commercial Engine Alert Bulletin CEB-A-72-3124 initial issue dated November 15, 1984, or Revision 1 dated December 16, 1985, and prerequisite CEB-A-72-3125 dated November 15, 1984, and Sikorsky ASB 76-71-7 dated November 9, 1984, or FAA-approved equivalents; or, install an Allison first stage turbine wheel internal energy absorbing ring P/N 23031909, or P/N 23032263, or FAA-approved equivalent, in accordance with Allison Commercial Engine Alert Bulletin CEB-A-72-3128 initial issue dated November 15, 1984, or Revision 1 dated September 30, 1985, and Sikorsky ASB 76-71-7 dated November 9, 1984, or FAA-approved equivalents.
NOTE: The engine manufacturer in Revision 1 dated December 16, 1985, to Allison CEB-A-72-3124 added an inspection of the first stage turbine wheel external energy absorbing ring turbine mount link P/N 23031441 for misalignment and mounting bracket P/N 23031446 for cracks at intervals of 25 hours time-in- service. While the FAA concurs with the desirability of this inspection, it is not made mandatory by this AD.(2) Within the next 25 hours time-in-service after the compliance with (a), above, and thereafter at intervals not to exceed 25 hours time-in-service, inspect the Sikorsky Model S-76A helicopter engine compartment protective shields in accordance with Chapter 5 of Sikorsky Airworthiness and Inspection Requirements Manual, Publication No. SA 4047-76-2-1 dated November 12, 1984, or FAA-approved equivalent.
(3) At the next engine repair/overhaul shop visit after December 18, 1984, but not later than November 30, 1986, update the engines to the "Allison Assured Engine" configuration and continue to maintain in accordance with Allison Commercial Service Letter, CSL-3068 initial issue dated October 1, 1985, or CSL- 3068, Revision 1, dated September 30, 1985, or FAA-approved equivalent with the following exception to the November 30, 1986, compliance deadline:
At the next engine repair/overhaul shop visit after December 18, 1984, but not later than March 30, 1986, inspect and modify the 29-34 labyrinth seal for engines with more than 100 hours time-in-service since turbine overhaul or repair, in accordance with Allison CEB-A-72-3127, Revision 2, dated April 3, 1985, or prior issues and CEB-A-72-3131, Revision 1, dated April 22, 1985, or initial issue, respectively, or FAA-approved equivalents.
NOTE: The date November 30, 1986, that appears in paragraph 4B and 8 of Allison Commercial Service Letter CSL-3068, Revision 1, dated September 30, 1985, should read March 30, 1986.
(4) At the next turbine repair/overhaul shop visit after the effective date of this AD, but not later than November 30, 1986, perform the following:
(i) Install first stage turbine wheel internal energy absorbing ring P/N 23031909, or P/N 23032263, or FAA-approved equivalent, in accordance with Allison CEB-A-72-3128, Revision 1, dated September 30, 1985, or initial issue, or FAA-approved equivalent.
(ii) Replace existing second stage turbine wheel P/N 6892762, or P/N 689822,or P/N 23004233 with P/N 23032280, or FAA-approved equivalent, in accordance with Allison CEB-A-72-3132, dated February 1, 1985, or FAA-approved equivalent.
(iii) Remove engine external energy absorbing ring P/N 23001910, L.H. or P/N 23001920, R.H., as appropriate, in accordance with Allison CEB-72-3136 dated July 31, 1985, or FAA-approved equivalent.
(iv) The Sikorsky Model S-76A helicopter engine compartment protective shields, P/N 76070-20077-013 or P/N 76070-20077-014, may be removed in accordance with Sikorsky Customer Service Notice No. 76-158 dated January 14, 1985, after compliance with Paragraphs (a)(4)(i), (ii), and (iii) above. NOTE: The engine containment configurations 1 thru 4, and authorized configuration mixes listed in Appendix 1 of Sikorsky Customer Service Notice No. 76-158 dated January 14, 1985, continue to be FAA-approved until November 30, 1986; after this date only configurations 3 and 4 are authorized per Paragraphs (a)(1)(i) and (a)(4) of this AD for Allison Model 250-C30 and -C30S/Sikorsky Model S-76A installations.
(b) Allison Model 250-C30, -C30L, -C30M, -C30P, and -C30S engines installed in aircraft other than Sikorsky Aircraft Model S-76A helicopters
At the next turbine repair/overhaul shop visit after the effective date of this AD, but not later than November 30, 1987, perform the following:
(1) Install first stage turbine wheel internal energy absorbing ring P/N 23031909, or P/N 23032263, or FAA-approved equivalent, in accordance with Allison CEB-A-72-3128, Revision 1, dated September 30, 1985, or initial issue, or FAA-approved equivalent.
(2) Replace existing second stage turbine wheel P/N 6892762, or P/N 6898922, or P/N 23004233 with P/N 23032280, or FAA-approved equivalent, in accordance with Allison CEB-A-72-3137, Revision 1, dated May 3, 1985, or initial issue, or FAA-approved equivalent.
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.
Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018.
Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Chicago Aircraft Certification Office, may adjust the compliance time specified in this AD.
The manufacturers' specifications and procedures, identified and described in this document, are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1): Sikorsky Alert Service Bulletin 76-71-7 dated November 9, 1984 Sikorsky Airworthiness and Inspection Requirements Manual, Publication No. SA 4047-76-2-1 dated November 12, 1984
Sikorsky Customer Service Notice 76-158 dated January 14, 1985
Allison CSL-3068, Rev. 1, dated September 15, 1985
Allison CSL-A-3062, Rev. 1, dated January 15, 1985
Allison CSL-A-3066, Rev. 1, dated January 15, 1985
Allison CEB-A-72-3124, Rev. 1, dated December 16, 1985
Allison CEB-A-72-3125 dated November 15, 1984
Allison CEB-A-72-3127, Rev. 2, dated April 3, 1985
Allison CEB-A-72-3128, Rev. 1, dated September 30, 1985
Allison CEB-A-72-3131, Rev. 1, dated April 22, 1985
Allison CEB-A-72-3132 dated February 1, 1985
Allison CEB-A-72-3136 dated July 31, 1985
Allison CEB-A-72-3137, Rev. 1, dated May 3, 1985
All persons affected by this directive who have not already received these documents from the manufacturers may obtain copies upon request to Allison Gas Turbine Division, General Motors Corp., P.O. Box 420, Indianapolis, Indiana 46206-0420; and Sikorsky Aircraft, Division of United Technologies Corp., North Main Street, Stratford, Connecticut 06601. These documents also may be examined at the Office of Regional Counsel, FAA, ATTN: Rules Docket No. 84-ANE-21, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays, except Federal holidays, between 8:00 a.m. and 4:30 p.m.
This amendment supersedes AD 84-24-02, Amendment 39-4957, 49 FR 48531, effective December 18, 1984.
This amendment becomes effective on October 3, 1986.
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88-03-09: 88-03-09 MCDONNELL DOUGLAS: Amendment 39-5839. Applies to McDonnell Douglas Model DC-9-81, -82, and -83 series airplanes, as listed in McDonnell Douglas Service Bulletin 34-177, dated April 28, 1987, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo prevent erroneous information from being transmitted to the Digital Flight Guidance Computer (DFGC) from the Digital Air Data computer (DADC) in the event of an electrical transient, accomplish the following: \n\n\tA.\tWithin 12 months after the effective date of this airworthiness directive (AD), inspect Honeywell P/N HG280D80 DADC in affected airplanes to determine if Modification 8 has been installed, in accordance with Part 2 of the Accomplishment Instructions of McDonnell Douglas Service Bulletin 34-177, dated April 28, 1987, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\t1.\tIf Modification 8 has been installed and identified, no further action is necessary. \n\n\t\t2.\tIf Modification 8 has been installed but not identified, identify the DADC in accordance with the service bulletin. \n\n\t\t3.\tIf Modification 8 has not been installed, modify and identify the DADC in accordance with the service bulletin. \n\n\tB.\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\tC.\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 information from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director of Publications, C1-L00 (54-60); or Honeywell, Incorporated, Commercial Aviation Division Technical Services, Mail Station MN23-6345, P.O. Box 889, Minneapolis, Minnesota 55440. 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 March 11, 1988.
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