AD 90-15-11
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | Pratt & Whitney Division | JT9D-7R4D1 | PRATT & WHITNEY Models JT9D-7R4D1, -7R4E1, and -7R4H1 Series Engines |
| engine | Pratt & Whitney Division | JT9D-7R4E1 | PRATT & WHITNEY Models JT9D-7R4D1, -7R4E1, and -7R4H1 Series Engines |
| engine | Pratt & Whitney Division | JT9D-7R4H1 | PRATT & WHITNEY Models JT9D-7R4D1, -7R4E1, and -7R4H1 Series Engines |
Unsafe Condition
Engine overtemperature, loss of power, or engine inflight shutdown due to fuel control unit deceleration schedule, 3.0 bleed valve cylinder, and engine vane and bleed control issues.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Adjust fuel control unit deceleration schedule and reidentify FCU; modify 3.0 bleed valve cylinder; inspect 3.0 bleed valve linkages and remove engines with worn linkages before 5 cycles; adjust EVBC to specified EPR bleed trims; incorporate EVBC and FCU modifications; install 3.0 bleed dampers at next shop visit; restore first stage compressor blades at fan module overhauls.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 30 calendar days or 150 flight cycles (whichever occurs first) after the effective date for initial adjustments; within 60 calendar days or 300 flight cycles for EVBC adjustments; within one year for EVBC and FCU modifications; at next shop visit for 3.0 bleed dampers; at every fan module overhaul for compressor blade restoration.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Pratt & Whitney JT9D-7R4D1, -7R4E1, and -7R4H1 series engines installed on Airbus Industries A300/A310 aircraft.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Fuel Control Unit
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_90-15-11.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-15-11 Document Type: AD Final Rules Docket Number: 89-ANE-33-AD Subject Heading: PRATT & WHITNEY Models JT9D-7R4D1, -7R4E1, and -7R4H1 Series Engines Subject: Fuel Control Unit Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/16/1990 Make: Pratt & Whitney Division Model: JT9D-7R4D1 | JT9D-7R4E1 | JT9D-7R4H1 Product Type: Engine Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 90-15-11 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 89-ANE-33-AD AMENDMENT: 39-6474 AD NUMBER: 90-15-11 SUBJECT HEADING: PRATT & WHITNEY Models JT9D-7R4D1, -7R4E1, and -7R4H1 Series Engines ACTION: SUMMARY: DATES: Effective July 16, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-15-11 PRATT & WHITNEY: Amendment 39-6474. Docket No. 89-ANE-33-AD. Applicability: Pratt & Whitney (PW) JT9D-7R4D1, -7R4E1, and -7R4H1 series turbofan engines installed on Airbus Industries A300/A310 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent engine overtemperature and loss of power or engine inflight shutdown, accomplish the following: (a) Within the next 30 calendar days or 150 flight cycles, whichever occurs first after the effective date of this AD, accomplish the following: (1) Adjust the deceleration schedule of the fuel control unit (FCU), and reidentify the FCU, in accordance with the applicable instructions of Appendix 1 of this AD. If cycling bleeds occur as a result of the decel schedule uptrim, downtrim the decel schedule in accordance with the applicable instructions of Appendix 2 to this AD. (2) Modify the 3.0 bleed valve cylinder, Part Number (P/N) 806885 or P/N 774300, in accordance with the instructions of Appendix 3 or Appendix 4 of this AD, as applicable. (3) Inspect 3.0 bleed valve linkages for wear in accordance with the instructions of Appendix 5 to this AD, and accomplish the following: (i) Remove engines with worn 3.0 valve linkage prior to accumulating 5 cycles in service (CIS) since last inspection and replace with a serviceable engine. (ii) Reinspect linkages found serviceable in accordance with the inspection requirement of paragraph (a)(3) above, at intervals not to exceed 3,000 hours since last inspection. (b) Within the next 60 calendar days or 300 flight cycles, whichever occurs first after the effective date of this AD, accomplish the following: Adjust the engine vane and bleed control (EVBC), Hamilton Standard, P/N 776555-3, to the 1.27 engine pressure ratio (EPR) bleed trim and P/N 776555-5 to the 1.32 EPR bleed trim, in accordance with the instructions of Appendix 6, Appendix 7, or Appendix 8 to this AD, as applicable. Engines which have had no 3.0 bleed or valve schedule adjustments since last trimmed in the test cell (P/N 776555-3 EVBC trimmed to 1.27 EPR or P/N 776555-5 EVBC trimmed to 1.32 EPR) are exempt from this requirement. (c) Incorporate the following modifications to upgrade the EVBC to Hamilton Standard P/N 776555-5, within one year from the effective date of this AD, by accomplishing the following: (1) Incorporate the fluid drain between sensor servo piston chevron seals, in accordance with the instructions of Appendix 9 to this AD. (2) Incorporate the pilot valve spring, P/N 801040-1, in accordance with the instructions of Appendix 10 to this AD. (3) Incorporate the decel bleed reset piston spring, P/N 801073-1, in accordance with the instructions of Appendix 11 to this AD. (4) Incorporate the 3.0 bleed cam, P/N 765357-11, and recalibrate the control, in accordance with the instructions of Appendix 12 to this AD. (5) Incorporate the actuator valve, P/N 800997-1, in accordance with the instructions of Appendix 13 to this AD; or remove actuator valve, P/N 728149-3, and replace with a new or serviceable actuator valve, P/N 728149-3. Replacement actuator valve, P/N 728149-3, must be removed from service at or prior to accumulating 10,000 hours since new. (6) Adjust EVBC to 1.32 EPR bleed trim, in accordance with paragraph (b)(1) above. (d) Modify FCU, Hamilton Standard P/N 782960-1, and P/N 782960-2, within one year from the effective date of this AD by accomplishing the following: (1) Incorporate the decel cam, P/N 774538-15, in accordance with the instructions of Appendix 14 of this AD. (2) Revise the test procedure for the decel bleed override, in accordance with the instructions of Appendix 15 of this AD. (e) Install 3.0 bleed dampers, in accordance with PW Service Bulletin (SB) JT9D-7R4-72-336, Revision 5, dated June 23, 1988, at the next shop visit. Installation of 3.0 bleed dampers terminates the reinspection requirements of paragraph (a)(3)(ii) above. NOTE: For the purpose of this AD, the definition of "shop visit" is any time the engine or module is in a maintenance shop capable of complying with the PW SB instructions, regardless of the planned maintenance action or the reason for engine removal. (f) Restore the leading edge of the first stage compressor blades in accordance with PW Engine Manual, P/N 785058, Chapter/Section 72-31-02, Repair-19, Pages 901 through 912, dated June 15, 1990, at the next fan module overhaul, after the effective date of this AD and thereafter at every fan module overhaul. NOTE: For the purpose of this AD, the definition of "fan module overhaul" is anytime the fan module is disassembled, inspected, and repaired, in accordance with PW Engine Manual. (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 times 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. First stage compressor blade restoration and 3.0 bleed damper installation shall be done in accordance with the following PW documents: Document No. Page Number Issue/Revision Date Engine Manual 901 thru 914 ---- June 15, 1990 -PW785058 JT9D-7R4-72-336 1, 3, 4, 8, 9, 5 June 23, 1988 10, 11 thru 20 4 August 28, 1987 2 3 June 8, 1987 5, 6, 7 Original March 2, 1987 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 Pratt & Whitney Publications Department, P.O. Box 611, Middletown, Connecticut 06457. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, NW, Room 8301, Washington, DC 20591. This amendment (39-6474, AD 90-15-11) becomes effective on July 16, 1990. Appendix 1 NOTE: This appendix consists of material from: Pratt & Whitney (PW) Special Instructions (SI) 59F-89 (applicable to JT9D-7R4D1, E1 (AI-500 series)), dated July 10, 1989, and SI 61F-89 (applicable to JT9D-7R4E1, H1 (AI-600 series)), dated July 10, 1989. Appendix 2 NOTE: This appendix consists of material from: PW SI 60F-89 (applicable to JT9D-7R4D1, E1 (AI-500 series)), dated July 10, 1989, and 62F-89 [applicable to JT9D-7R4E1, H1 (AI-600 series)), dated July 10, 1989. Appendix 3 NOTE: This appendix consists of material from: PW Service Bulletin (SB) JT9D-7R4-75-98, dated January 19, 1988. Appendix 4 NOTE: This appendix consists of material from: PW SI 58F-89, dated June 16, 1989. Appendix 5 NOTE: This appendix consists of material from: PW Maintenance Manual, Chapter/Section 72-00-00 Inspection/Check -06, dated September 15, 1986. Appendix 6 NOTE: This appendix consists of material from: AI A300-600/A310 AMM Chapter/Section 71-00-00, Test Number 10, Temporary Revision No. 71-029, dated January 10, 1989. Appendix 7 NOTE: This appendix consists of material from: PW SI 82F-88, Revision A, dated November 16, 1988. Appendix 8 NOTE: This appendix consists of material from: PW SI 87-88, dated August 26, 1988. Appendix 9 NOTE: This appendix consists of material from: Hamilton Standard (HS) SB GTA9-75-9, Revision 1, dated October 14, 1984. Appendix 10 NOTE: This appendix consists of material from: HS SB GTA9-75-16, dated March 20, 1988. Appendix 11 NOTE: This appendix consists of material from: HS SB GTA9-75-17, dated March 31, 1988. Appendix 12 NOTE: This appendix consists of material from: HS SB GTA9-75-18, Revision 1, dated January 15, 1989. Appendix 13 NOTE: This appendix consists of material from: HS SB GTA9-75-19, dated August 12, 1988. Appendix 14 NOTE: This appendix consists of material from: HS SB JFC68-10-10, Revision 1, dated November 15, 1989. Appendix 15 NOTE: This appendix consists of material from: HS SB JFC68-10-9, dated March 31, 1988. FOOTER:
Document Text
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AD Final Rules - DRS_90-15-11.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 90-15-11 Document Type: AD Final Rules Docket Number: 89-ANE-33-AD Subject Heading: PRATT & WHITNEY Models JT9D-7R4D1, -7R4E1, and -7R4H1 Series Engines Subject: Fuel Control Unit Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 07/16/1990 Make: Pratt & Whitney Division Model: JT9D-7R4D1 | JT9D-7R4E1 | JT9D-7R4H1 Product Type: Engine Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 90-15-11 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 89-ANE-33-AD AMENDMENT: 39-6474 AD NUMBER: 90-15-11 SUBJECT HEADING: PRATT & WHITNEY Models JT9D-7R4D1, -7R4E1, and -7R4H1 Series Engines ACTION: SUMMARY: DATES: Effective July 16, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 90-15-11 PRATT & WHITNEY: Amendment 39-6474. Docket No. 89-ANE-33-AD. Applicability: Pratt & Whitney (PW) JT9D-7R4D1, -7R4E1, and -7R4H1 series turbofan engines installed on Airbus Industries A300/A310 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent engine overtemperature and loss of power or engine inflight shutdown, accomplish the following: (a) Within the next 30 calendar days or 150 flight cycles, whichever occurs first after the effective date of this AD, accomplish the following: (1) Adjust the deceleration schedule of the fuel control unit (FCU), and reidentify the FCU, in accordance with the applicable instructions of Appendix 1 of this AD. If cycling bleeds occur as a result of the decel schedule uptrim, downtrim the decel schedule in accordance with the applicable instructions of Appendix 2 to this AD. (2) Modify the 3.0 bleed valve cylinder, Part Number (P/N) 806885 or P/N 774300, in accordance with the instructions of Appendix 3 or Appendix 4 of this AD, as applicable. (3) Inspect 3.0 bleed valve linkages for wear in accordance with the instructions of Appendix 5 to this AD, and accomplish the following: (i) Remove engines with worn 3.0 valve linkage prior to accumulating 5 cycles in service (CIS) since last inspection and replace with a serviceable engine. (ii) Reinspect linkages found serviceable in accordance with the inspection requirement of paragraph (a)(3) above, at intervals not to exceed 3,000 hours since last inspection. (b) Within the next 60 calendar days or 300 flight cycles, whichever occurs first after the effective date of this AD, accomplish the following: Adjust the engine vane and bleed control (EVBC), Hamilton Standard, P/N 776555-3, to the 1.27 engine pressure ratio (EPR) bleed trim and P/N 776555-5 to the 1.32 EPR bleed trim, in accordance with the instructions of Appendix 6, Appendix 7, or Appendix 8 to this AD, as applicable. Engines which have had no 3.0 bleed or valve schedule adjustments since last trimmed in the test cell (P/N 776555-3 EVBC trimmed to 1.27 EPR or P/N 776555-5 EVBC trimmed to 1.32 EPR) are exempt from this requirement. (c) Incorporate the following modifications to upgrade the EVBC to Hamilton Standard P/N 776555-5, within one year from the effective date of this AD, by accomplishing the following: (1) Incorporate the fluid drain between sensor servo piston chevron seals, in accordance with the instructions of Appendix 9 to this AD. (2) Incorporate the pilot valve spring, P/N 801040-1, in accordance with the instructions of Appendix 10 to this AD. (3) Incorporate the decel bleed reset piston spring, P/N 801073-1, in accordance with the instructions of Appendix 11 to this AD. (4) Incorporate the 3.0 bleed cam, P/N 765357-11, and recalibrate the control, in accordance with the instructions of Appendix 12 to this AD. (5) Incorporate the actuator valve, P/N 800997-1, in accordance with the instructions of Appendix 13 to this AD; or remove actuator valve, P/N 728149-3, and replace with a new or serviceable actuator valve, P/N 728149-3. Replacement actuator valve, P/N 728149-3, must be removed from service at or prior to accumulating 10,000 hours since new. (6) Adjust EVBC to 1.32 EPR bleed trim, in accordance with paragraph (b)(1) above. (d) Modify FCU, Hamilton Standard P/N 782960-1, and P/N 782960-2, within one year from the effective date of this AD by accomplishing the following: (1) Incorporate the decel cam, P/N 774538-15, in accordance with the instructions of Appendix 14 of this AD. (2) Revise the test procedure for the decel bleed override, in accordance with the instructions of Appendix 15 of this AD. (e) Install 3.0 bleed dampers, in accordance with PW Service Bulletin (SB) JT9D-7R4-72-336, Revision 5, dated June 23, 1988, at the next shop visit. Installation of 3.0 bleed dampers terminates the reinspection requirements of paragraph (a)(3)(ii) above. NOTE: For the purpose of this AD, the definition of "shop visit" is any time the engine or module is in a maintenance shop capable of complying with the PW SB instructions, regardless of the planned maintenance action or the reason for engine removal. (f) Restore the leading edge of the first stage compressor blades in accordance with PW Engine Manual, P/N 785058, Chapter/Section 72-31-02, Repair-19, Pages 901 through 912, dated June 15, 1990, at the next fan module overhaul, after the effective date of this AD and thereafter at every fan module overhaul. NOTE: For the purpose of this AD, the definition of "fan module overhaul" is anytime the fan module is disassembled, inspected, and repaired, in accordance with PW Engine Manual. (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 times 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. First stage compressor blade restoration and 3.0 bleed damper installation shall be done in accordance with the following PW documents: Document No. Page Number Issue/Revision Date Engine Manual 901 thru 914 ---- June 15, 1990 -PW785058 JT9D-7R4-72-336 1, 3, 4, 8, 9, 5 June 23, 1988 10, 11 thru 20 4 August 28, 1987 2 3 June 8, 1987 5, 6, 7 Original March 2, 1987 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 Pratt & Whitney Publications Department, P.O. Box 611, Middletown, Connecticut 06457. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, NW, Room 8301, Washington, DC 20591. This amendment (39-6474, AD 90-15-11) becomes effective on July 16, 1990. Appendix 1 NOTE: This appendix consists of material from: Pratt & Whitney (PW) Special Instructions (SI) 59F-89 (applicable to JT9D-7R4D1, E1 (AI-500 series)), dated July 10, 1989, and SI 61F-89 (applicable to JT9D-7R4E1, H1 (AI-600 series)), dated July 10, 1989. Appendix 2 NOTE: This appendix consists of material from: PW SI 60F-89 (applicable to JT9D-7R4D1, E1 (AI-500 series)), dated July 10, 1989, and 62F-89 [applicable to JT9D-7R4E1, H1 (AI-600 series)), dated July 10, 1989. Appendix 3 NOTE: This appendix consists of material from: PW Service Bulletin (SB) JT9D-7R4-75-98, dated January 19, 1988. Appendix 4 NOTE: This appendix consists of material from: PW SI 58F-89, dated June 16, 1989. Appendix 5 NOTE: This appendix consists of material from: PW Maintenance Manual, Chapter/Section 72-00-00 Inspection/Check -06, dated September 15, 1986. Appendix 6 NOTE: This appendix consists of material from: AI A300-600/A310 AMM Chapter/Section 71-00-00, Test Number 10, Temporary Revision No. 71-029, dated January 10, 1989. Appendix 7 NOTE: This appendix consists of material from: PW SI 82F-88, Revision A, dated November 16, 1988. Appendix 8 NOTE: This appendix consists of material from: PW SI 87-88, dated August 26, 1988. Appendix 9 NOTE: This appendix consists of material from: Hamilton Standard (HS) SB GTA9-75-9, Revision 1, dated October 14, 1984. Appendix 10 NOTE: This appendix consists of material from: HS SB GTA9-75-16, dated March 20, 1988. Appendix 11 NOTE: This appendix consists of material from: HS SB GTA9-75-17, dated March 31, 1988. Appendix 12 NOTE: This appendix consists of material from: HS SB GTA9-75-18, Revision 1, dated January 15, 1989. Appendix 13 NOTE: This appendix consists of material from: HS SB GTA9-75-19, dated August 12, 1988. Appendix 14 NOTE: This appendix consists of material from: HS SB JFC68-10-10, Revision 1, dated November 15, 1989. Appendix 15 NOTE: This appendix consists of material from: HS SB JFC68-10-9, dated March 31, 1988. FOOTER:
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