AD 2003-10-03R1
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | Rolls-Royce plc | RB211-535E4-B-37 | Airworthiness Directives; Rolls-Royce plc Model RB211 Turbofan Engines |
| engine | Rolls-Royce plc | RB211-535E4-B-75 | Airworthiness Directives; Rolls-Royce plc Model RB211 Turbofan Engines |
Unsafe Condition
Machining-induced cracking of the high pressure (HP) turbine discs could cause an uncontained HP turbine disc failure and damage to the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Remove from service certain high pressure (HP) turbine discs before they reach newly established life limits.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Effective June 20, 2003
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Rolls-Royce plc Model RB211-535E4-B-37 and RB211-535E4-B-75 turbofan engines
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
High pressure (HP) turbine discs
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - 031003R1.pdf Copy URL Document Versions Feedback DetailsAttachments/Public Comments AD Number: 2003-10-03R1 Document Type: AD Final Rules Docket Number: 2002-NE-12-AD Subject Heading: Airworthiness Directives; Rolls-Royce plc Model RB211 Turbofan Engines Subject: High pressure (HP) turbine discs Status: Current Citation: Federal Register: June 4, 2003 (Volume 68, Number 107) Citation Publish Date: 06/04/2003 Effective Date: 06/20/2003 Make: Rolls-Royce plc Model: RB211-535E4-B-37 | RB211-535E4-B-75 Product Type: Engine Product Subtype: Affected AD: Superseded AD: 2003-10-03 Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Automatic Zoom Actual Size Page Fit Page Width 50% 75% 100% 125% 150% 200% 300% 400% 125% of 5 [Federal Register: June 4, 2003 (Volume 68, Number 107)] [Rules and Regulations] [Page 33358-33360] From the Federal Register Online via GPO Access [wais.access.gpo.gov] [DOCID:fr04jn03-6] ––––––––––––––––––––––––––––––––––– DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2002-NE-12-AD; Amendment 39-13182; AD 2003-10-03R1] RIN 2120-AA64 Airworthiness Directives; Rolls-Royce plc Model RB211 Turbofan Engines AGENCY: Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. ––––––––––––––––––––––––––––––––––– SUMMARY: This amendment revises an existing airworthiness directive (AD) that is applicable to Rolls-Royce plc (RR) model RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines. The existing AD will become effective on June 20, 2003, and requires removal from service of certain high pressure (HP) turbine discs before they reach newly established life limits. This amendment requires the same actions, but removes the model RB211-535E4-37 turbofan engine from the applicability. This revision to the existing AD is prompted by further data gathering by the FAA that demonstrates that the model RB211-535E4-37 turbofan engine is not affected by machining-induced cracking within the currently published life of the HP turbine disc. The actions specified in this AD are intended to prevent machining-induced cracking of the HP turbine disc which could cause an uncontained HP turbine disc failure and damage to the airplane. DATES: Effective June 20, 2003. Comments for inclusion in the Rules Docket must be received on or before August 4, 2003. ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2002-NE-12-AD, 12 New England Executive Park, Burlington, MA 01803-5299. Comments may be inspected at this location, by appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. Comments may also be sent via the Internet using the following address: 9-ane- adcomment@faa.gov. Comments sent via the Internet must contain the docket number in the subject line. Information regarding this action may be examined, by appointment, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. 1 FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299, telephone (781) 238-7178; fax (781) 238-7199. SUPPLEMENTARY INFORMATION: On May 9, 2003, the FAA issued AD 2003-10-03, Amendment 39-13148 (68 FR 26481, May 16, 2003), to require removal from service of certain HP turbine discs in RR model RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines, before the discs reach newly established life limits. That action was prompted by the manufacturer's inspections and analysis of HP turbine discs that have accumulated high cycles. That AD will become effective on June 20, 2003. The FAA is revising this amendment to remove the model RB211-535E4-37 turbofan engine from the applicability. The FAA has received additional details of the engineering analysis based on field inspection data from the Civil Aviation Authority (CAA), which is the aviation authority for the U.K., and has determined that the model RB211-535E4-37 turbofan engine is not affected by machining-induced cracking within the currently published life of the HP turbine disc. This revised AD will be effective on June 20, 2003, in order to reduce the burden on operators. Bilateral Airworthiness Agreement This engine model is manufactured in the U.K. and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the CAA has kept the FAA informed of the situation described above. The FAA has examined the findings of the CAA, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. FAA's Determination of an Unsafe Condition and Required Actions Since an unsafe condition has been identified that is likely to exist or develop on other RR model RB211-535E4-B-37 and RB211-535E4-B-75 turbofan engines of the same type design, this AD is being issued to prevent machining-induced cracking of the HP turbine disc which could cause an uncontained HP turbine disc failure and damage to the airplane. This AD requires removal from service of certain HP turbine discs before they reach newly established life limits. Immediate Adoption of This AD Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are unnecessary, and that good cause exists for making this amendment effective in less than 30 days. Comments Invited Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications should identify the Rules Docket number and be submitted in triplicate to the address specified under the caption ADDRESSES. All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed. 2
Document Text
Show stored source text (verify against official source)
AD Final Rules - 031003R1.pdf Copy URL Document Versions Feedback DetailsAttachments/Public Comments AD Number: 2003-10-03R1 Document Type: AD Final Rules Docket Number: 2002-NE-12-AD Subject Heading: Airworthiness Directives; Rolls-Royce plc Model RB211 Turbofan Engines Subject: High pressure (HP) turbine discs Status: Current Citation: Federal Register: June 4, 2003 (Volume 68, Number 107) Citation Publish Date: 06/04/2003 Effective Date: 06/20/2003 Make: Rolls-Royce plc Model: RB211-535E4-B-37 | RB211-535E4-B-75 Product Type: Engine Product Subtype: Affected AD: Superseded AD: 2003-10-03 Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Automatic Zoom Actual Size Page Fit Page Width 50% 75% 100% 125% 150% 200% 300% 400% 125% of 5 [Federal Register: June 4, 2003 (Volume 68, Number 107)] [Rules and Regulations] [Page 33358-33360] From the Federal Register Online via GPO Access [wais.access.gpo.gov] [DOCID:fr04jn03-6] ––––––––––––––––––––––––––––––––––– DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2002-NE-12-AD; Amendment 39-13182; AD 2003-10-03R1] RIN 2120-AA64 Airworthiness Directives; Rolls-Royce plc Model RB211 Turbofan Engines AGENCY: Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. ––––––––––––––––––––––––––––––––––– SUMMARY: This amendment revises an existing airworthiness directive (AD) that is applicable to Rolls-Royce plc (RR) model RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines. The existing AD will become effective on June 20, 2003, and requires removal from service of certain high pressure (HP) turbine discs before they reach newly established life limits. This amendment requires the same actions, but removes the model RB211-535E4-37 turbofan engine from the applicability. This revision to the existing AD is prompted by further data gathering by the FAA that demonstrates that the model RB211-535E4-37 turbofan engine is not affected by machining-induced cracking within the currently published life of the HP turbine disc. The actions specified in this AD are intended to prevent machining-induced cracking of the HP turbine disc which could cause an uncontained HP turbine disc failure and damage to the airplane. DATES: Effective June 20, 2003. Comments for inclusion in the Rules Docket must be received on or before August 4, 2003. ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2002-NE-12-AD, 12 New England Executive Park, Burlington, MA 01803-5299. Comments may be inspected at this location, by appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. Comments may also be sent via the Internet using the following address: 9-ane- adcomment@faa.gov. Comments sent via the Internet must contain the docket number in the subject line. Information regarding this action may be examined, by appointment, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. 1 FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299, telephone (781) 238-7178; fax (781) 238-7199. SUPPLEMENTARY INFORMATION: On May 9, 2003, the FAA issued AD 2003-10-03, Amendment 39-13148 (68 FR 26481, May 16, 2003), to require removal from service of certain HP turbine discs in RR model RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines, before the discs reach newly established life limits. That action was prompted by the manufacturer's inspections and analysis of HP turbine discs that have accumulated high cycles. That AD will become effective on June 20, 2003. The FAA is revising this amendment to remove the model RB211-535E4-37 turbofan engine from the applicability. The FAA has received additional details of the engineering analysis based on field inspection data from the Civil Aviation Authority (CAA), which is the aviation authority for the U.K., and has determined that the model RB211-535E4-37 turbofan engine is not affected by machining-induced cracking within the currently published life of the HP turbine disc. This revised AD will be effective on June 20, 2003, in order to reduce the burden on operators. Bilateral Airworthiness Agreement This engine model is manufactured in the U.K. and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the CAA has kept the FAA informed of the situation described above. The FAA has examined the findings of the CAA, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. FAA's Determination of an Unsafe Condition and Required Actions Since an unsafe condition has been identified that is likely to exist or develop on other RR model RB211-535E4-B-37 and RB211-535E4-B-75 turbofan engines of the same type design, this AD is being issued to prevent machining-induced cracking of the HP turbine disc which could cause an uncontained HP turbine disc failure and damage to the airplane. This AD requires removal from service of certain HP turbine discs before they reach newly established life limits. Immediate Adoption of This AD Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are unnecessary, and that good cause exists for making this amendment effective in less than 30 days. Comments Invited Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications should identify the Rules Docket number and be submitted in triplicate to the address specified under the caption ADDRESSES. All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed. 2
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Retrieved: Apr 8, 2026
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