{"id":"F2009L00932","name":"AD/CF6/71 - Life Limited Parts","slug":"ad-cf6-71-life-limited-parts","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":78370,"registerId":"commonwealth-F2009L00932-current","compilationNumber":null,"startDate":"2026-04-02","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"General Electric Turbine Engines - CF6 S","sectionType":"division","heading":"General Electric Turbine Engines - CF6 Series","content":"### General Electric Turbine Engines - CF6 Series\n\n| AD/CF6/71 | Life Limited Parts | 4/2009 |\n| --------- | ------------------ | ------ |\n\n```html\n

Applicability:

General Electric Company CF6-80A, CF6-80C2, and CF6-80E1 series turbofan engines.

Note 1: These engines are installed on, but not limited to, Airbus A300, A310, and A330 series, Boeing 747 and 767 series, and McDonnell Douglas MD-11 series aeroplanes.

Requirement:

1. Revise the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA), and for air carrier operations revise the approved continuous airworthiness maintenance program, by adding the following: ''MANDATORY INSPECTIONS'' as detailed in Table 1 of this AD.

Table 1

Part Nomenclature

Part Number (P/N)

Inspect per Engine Manual Inspection Chapter

For CF6-80A Engines:

Disk, Fan Rotor,
Stage 1

All

72-21-03 Paragraph 3. Fluorescent-Penetrant Inspect, and 72-21-03 Paragraph 4. Eddy Current Inspect

Fan Forward Shaft

All

72-21-05 Paragraph 2. Magnetic Particle Inspect

Fan Mid Shaft

All

72-24-01 Paragraph 2. Magnetic Particle Inspect

Disk, HPC Rotor,
Stage One

All

72-31-04 Paragraph 3. Fluorescent-Penetrant Inspect

** Disk, HPC Rotor, Stage Two

All

72-31-05 Paragraph 4. Fluorescent-Penetrant Inspect

\n```\n\n```html\n

Spool, HPC Rotor, Stage3-9

All

72-31-06 Paragraph 3. Fluorescent-Penetrant Inspect

Disk, HPC Rotor,
Stage 10

All

72-31-07 Paragraph 3. Fluorescent-Penetrant Inspect

Spool, HPC Rotor,
Stage 11-14

All

72-31-08 Paragraph 3.A. Fluorescent-Penetrant Inspect

Rotating CDP Seal

All

72-31-10 Paragraph 3. Fluorescent-Penetrant Inspect

Disk Shaft, HPT Rotor Stage One

All

72-53-02 Paragraph 3. Fluorescent-Penetrant-Inspect per 70-32-02, and

72-53-02 Paragraph 6.C. Disk Rim Bolt Hole Eddy Current Inspection, and

72-53-02 Paragraph 6.D. Disk Bore Eddy Current Inspection

* Disk Shaft, HPT Rotor Stage One

All

72-53-02 Paragraph 6.E. Disk Dovetail Slot Bottom Eddy Current Inspection

* Disk Shaft, HPT Rotor, Stage One

P/Ns 2047M33G01 thru G10, and P/N 9362M58G11

72-53-02 Paragraph 7. Disk Dovetail Slot Bottom Aft Corner Chamfers Eddy Current Inspection

Disk, HPT Rotor,
Stage Two

All

72-53-06 Paragraph 3. Fluorescent-Penetrant Inspection, and

72-53-06 Paragraph 6. Eddy Current Inspection of Rim Bolt Holes for Cracks, and

72-53-06 Paragraph 7. Disk Bore Eddy Current Inspection

\n```\n\n```html\n

Disk, LPT Rotor
Stage 1-4

All

72-57-02 Paragraph 3. Fluorescent-Penetrant Inspection

Shaft, LPT Rotor

All

72-57-03 Paragraph 3. Fluorescent-Penetrant Inspection, and

72-57-03 Paragraph 6. Eddy Current Inspection

For All CF6-80C2 Engines:

Disk, Fan Rotor,
Stage 1

All

Task 72-21-03-200-000-004 Fluorescent-Penetrant Inspection, and

Task 72-21-03-200-000-008 Eddy Current Inspect Fan Rotor Disk Stage 1 Bore, Forward and Aft Hub Faces, and Bore Radii

Shaft, Fan Forward

All

Task 72-21-05-200-000-001 Fluorescent Penetrant Inspection, and

Task 72-21-05-200-000-005 Vent Hole Eddy Current Inspection

Fan Mid Shaft

All

Task 72-24-01-200-000-003 Magnetic Particle Inspection

HPCR Stage 1 Disk

All

Task 72-31-04-200-000-002 Fluorescent Penetrant Inspection

HPCR Stage 2 Disk

All

Task 72-31-05-200-000-002 Fluorescent Penetrant Inspection

HPCR Stage 3-9 Spool

All

Task 72-31-06-200-000-001 Fluorescent Penetrant Inspection

HPCR Stage 10 Disk

All

Task 72-31-07-200-000-001 Fluorescent Penetrant Inspection

HPCR Stage 11-14 Spool/Shaft

All

Task 72-31-08-200-000-002 Fluorescent Penetrant Inspection

No. 4 Bearing Rotating (CDP) Air Seal

All

Task 72-31-10-200-000-001 Fluorescent Penetrant Inspection or

Task 72-31-10-200-000-A01 Fluorescent Penetrant Inspection

HPCR Stage 10-14 Spool/Shaft

All

Task 72-31-22-200-000-002 Fluorescent Penetrant Inspection

** Disk/Shaft, HPT Rotor, Stage One

All

Task 72-53-02-200-000-001 (Inspection - Configuration 1), or Task 72-53-02-230-801 (Inspection - Configuration 2), Fluorescent-Penetrant Inspect, and

Task 72-53-02-200-000-005 (Inspection - Configuration 1), or Task 72-53-02-250-802 (Inspection - Configuration 2), Disk Rim Bolt Hole Eddy Current Inspection, and

Task 72-53-02-200-000-006 (Inspection - Configuration 1), or Task 72-53-02-250-803 (Inspection - Configuration 2), Disk Bore Area Eddy Current Inspection, and

\n```\n\n```html\n

Task 72-53-02-200-000-007 (Inspection - Configuration 1), or Task 72-53-02-250-804 (Inspection - Configuration 2), Disk Dovetail Slot Bottom Eddy Current

* Disk/Shaft, HPT Rotor, Stage One

P/N 1531M84G12 and P/Ns 2047M32G01 thru G07

Task 72-53-02-250-801 (Inspection - Configuration 1), Disk Dovetail Slot Bottom Aft Corner Chamfers Eddy Current Inspection

Disk, HPT Rotor,
Stage Two

All

Task 72-53-06-200-000-002 Fluorescent-Penetrant Inspect, and

Task 72-53-06-200-000-006 Disk Rim Bolt Hole Eddy Current Inspection, and

Task 72-53-06-200-000-007 Disk Bore Eddy Current Inspection

LPTR Stage 1-5 Disks

All

Task 72-57-02-200-000-001 Fluorescent-Penetrant Inspection

LPTR Shaft

All

Task 72-57-03-200-000-002 Fluorescent-Penetrant Inspect, and

Task 72-57-03-200-000-006 Eddy Current Inspection

\n```\n\n```html\n

For CF6-80C2 Engines configured with the R88DT Turbine (Models
CF6-80C2B2F, 80C2B4F, 80C2B6F, 80C2B7F, 80C2B8F):

Disk/Shaft, HPT Rotor, Stage One (R88DT, No Rim Bolt Holes)

All

Task 72-53-16-200-000-001 Fluorescent-Penetrant Inspect, and

Task 72-53-16-200-000-005 Disk Bore Area Eddy Current Inspection

Disk, HPT Rotor, Stage Two (R88DT, No Rim Bolt Holes)

All

Task 72-53-18-200-000-002 Fluorescent-Penetrant Inspect, and

Task 72-53-18-200-000-005 Disk Bore Area Eddy Current Inspection

Rotating Interstage Seal (R88DT)

All

Task 72-53-17-200-000-001 Fluorescent-Penetrant Inspect, and

Task 72-53-17-200-000-005 Seal Bore Area Eddy Current

Forward Outer Seal (R88DT)

All

Task 72-53-21-200-000-001 Fluorescent-Penetrant Inspect, and

Task 72-53-21-200-000-004 Seal Bore Area Eddy Current

For CF6-80E1 Engines:

Disk, Fan Rotor,
Stage One

All

Sub Task 72-21-03-230-051 Fluorescent-Penetrant Inspection, and

Sub Task 72-21-03-250-051 or 72-21-03-250-052 Disk Bore Eddy Current Inspection

\n```\n\n```html\n

Shaft, Fan

All

Sub Task 72-21-05-230-051 Fluorescent Penetrant Inspection, and

Sub Task 72-21-05-250-051 Vent Hole Eddy Current Inspection

Compressor Rotor,
Stage 1 Disk

All

Sub Task 72-31-04-230-051 Fluorescent Penetrant Inspection,

Compressor Rotor,
Stage 2 Disk

All

Sub Task 72-31-05-230-051 Fluorescent Penetrant Inspection

Compressor Rotor,
Stage 3-9 Spool

All

Sub Task 72-31-06-230-051 Fluorescent Penetrant Inspection

Compressor Rotor,
Stage 10 Disk (Pre SB
72-0150)

All

Sub Task 72-31-07-230-051 Fluorescent Penetrant Inspection

Compressor Rotor Spool/Shaft, Stage 11-14 (Pre SB 72-0150)

All

Sub Task 72-31-08-230-051 Fluorescent Penetrant Inspection

Compressor Rotor Spool/Shaft, Stage 10-14 (SB 72-0150)

All

Sub Task 72-31-23-230-052 Fluorescent Penetrant Inspection

Compressor Rotor No. 4 Bearing Rotating Air Seal (CDP Rotating Seal)

All

Sub Task 72-31-10-230-051 Fluorescent Penetrant Inspection

\n```\n\n```html\n

HPT Disk/Shaft,
Stage 1

All

Sub Task 72-53-02-230-051 Fluorescent-Penetrant Inspection, and

Sub Task 72-53-02-250-051 Eddy Current Inspection, Rim Bolt Holes, and

Sub Task 72-53-02-250-054 Eddy Current Inspection, Disk Bore

HPT Disk, Stage 2

All

Sub Task 72-53-06-230-051 Fluorescent-Penetrant Inspection, and

Sub Task 72-53-06-250-051 Eddy Current Inspection, Rim Bolt Holes, and

Sub Task 72-53-06-250-054 Eddy Current Inspection, Disk Bore

LPT Rotor Shaft

All

Sub Task 72-55-01-240-051 Magnetic Particle Inspect

LPT Disks, Stages 1-5

All

Sub Task 72-57-02-230-051 Fluorescent-Penetrant Inspect

LPT Rotor Torque Cone

All

Sub Task 72-57-03-220-051 Fluorescent-Penetrant Inspect

For CF6-80E1 Engines configured with the R88DT Turbine:

Disk/Shaft, HPT Rotor, Stage 1 (R88DT, No Rim Bolt Holes)

All

Sub Task 72-53-16-230-052 Fluorescent-Penetrant Inspect, and

Sub Task 72-53-16-250-051 Disk Bore Area Eddy Current Inspection

\n```\n\n```html\n

Disk, HPT Rotor, Stage 2 (R88DT, No Rim Bolt Holes)

All

Sub Task 72-53-18-230-051 Fluorescent-Penetrant Inspect, and

Sub Task 72-53-18-250-051 Disk Bore Area Eddy Current Inspection

** HPT Rotor Rotating Interstage Seal (R88DT)

All

Sub Task 72-53-17-230-056 Fluorescent-Penetrant Inspect, and

Sub Task 72-53-17-250-051 Seal Bore Area Eddy Current

HPT Rotor Forward Outer Seal (R88DT)

All

Sub Task 72-53-21-230-051 Fluorescent-Penetrant Inspect, and

Sub Task 72-53-21-250-051 Seal Bore Area Eddy Current

2. Perform inspections of the parts listed in Table 1 of this AD in accordance with the instructions provided in the applicable manual provisions.

Definition:

For the purposes of these mandatory inspections, piece-part opportunity means:

a) The part is considered completely disassembled when accomplished in accordance with the disassembly instructions in the manufacturer's engine manual; and

b) The part has accumulated more than 100 cycles-in-service since the last piece-part opportunity inspection, provided that the part was not damaged or related to the cause for its removal from the engine.

The parts added to the table of this AD are identified by an asterisk (*) that precedes the part nomenclature. Also, parts that have an Engine Manual Inspection Task and or Sub Task Number reference updated in the table of this AD, are identified by two asterisks (**) that precede the part nomenclature.

AMOC’s:

AMOC’s previously approved for FAA AD 2002-07-12, are also approved for this AD.

\n```\n\n| | Note 2: FAA AD 2009-04-10 Amdt 39-15816 dated 5 February 2009 refers.Note 3: This AD supersedes AD/CF6/46. |\n| ----------- | ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Compliance: | Fro Requirement 1 - Within 180 days after the effective date of this AD.For Requirement 2 - At each piece-part opportunity after Requirement 1 of this AD is completed. |\n| | This Airworthiness Directive becomes effective on 9 April 2009. |\n| Background: | This AD is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF6-80A, CF6-80C2, and CF6-80E1 series turbofan engines. That AD required revisions to the Airworthiness Limitations Section (ALS) of the manufacturer's Instructions for Continued Airworthiness (ICA) to include required inspection of selected critical life-limited parts at each piece-part exposure.This AD requires revisions to the CF6-80A, CF6-80C2, and CF6-80E1 series engines ALS sections of the manufacturer's manuals and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements, and to update certain Engine Manual Inspection Task and Sub Task Number references.This AD results from the need to require enhanced inspection of selected critical life-limited parts of CF6-80A, CF6-80C2, and CF6-80E1 series engines. The issuing of this AD is intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the aeroplane. |\n\n![](image.001.png) \nJames Coyne \nDelegate of the Civil Aviation Safety Authority\n\n27 February 2009","sortOrder":0},{"sectionNumber":"AD/CF6/71","sectionType":"part","heading":"AD/CF6/71","content":"## AD/CF6/71","sortOrder":1},{"sectionNumber":"Life Limited Parts","sectionType":"part","heading":"Life Limited Parts","content":"## Life Limited Parts","sortOrder":2},{"sectionNumber":"4/2009","sectionType":"part","heading":"4/2009","content":"## 4/2009","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":7,"scope_assessment":{"changed":true,"description":"This AD expands the prior directive’s coverage by adding additional mandatory inspections, updating many Engine Manual Task/Subtask references and identifying extra parts (marked by asterisks). It supersedes the earlier AD and incorporates FAA AMOC approvals, thereby broadening inspection requirements and updating implementation references compared with the prior instrument."},"complexity_factors":["Large, detailed parts list spanning three engine models (CF6-80A, -80C2, -80E1) with model-specific entries and R88DT-configured variants.","Extensive cross-references to many Engine Manual Task/Subtask numbers and specific non‑destructive test methods (fluorescent‑penetrant, eddy‑current, magnetic particle).","Requirement to revise the Airworthiness Limitations Section (ALS) and each air carrier’s approved continuous airworthiness maintenance program (administrative and procedural burden).","New procedural definition of \"piece‑part opportunity\" with a >100 cycles‑in‑service criterion (operational tracking and recordkeeping implications).","Supersedes an earlier AD and updates task/subtask references — implementers must map old to new references and affected configurations.","Acceptance of previously approved FAA AMOCs increases inter‑jurisdictional dependency and may constrain local alternative compliance approaches.","Compliance timing constraints (within 180 days for initial revisions; thereafter at each piece‑part opportunity) create scheduling pressures for MROs and operators."],"plain_english_summary":"This Airworthiness Directive requires operators of GE CF6-80A, CF6-80C2 and CF6-80E1 engines to amend the Airworthiness Limitations Section and approved maintenance programs to add mandatory inspections of specified life‑limited rotating parts and to carry out those inspections in accordance with the engine manual. It defines a \"piece‑part opportunity\" criterion and sets compliance timing. The rule affects aircraft operators and MROs who will organise, perform and pay for added inspections and program changes."},"flash_summary_failed":{"failed":true,"reason":"A positive credit balance is required for all requests, including BYOK, so fallback providers remain available. Add credits at https://vercel.com/d?to=%2F%5Bteam%5D%2F%7E%2Fai%3Fmodal%3Dtop-up to continue.","source":"analysis-cron"},"kimi_summary":{"content_quality":"ok","complexity_score":6,"scope_assessment":{"changed":true,"description":"This AD supersedes a previous directive (AD/CF6/46) and significantly expands the scope. The original AD required revisions to include inspection of selected critical life-limited parts. This version adds 'additional inspection requirements' and 'updates certain Engine Manual Inspection Task and Sub Task Number references.' The table has grown to cover more parts across more engine variants (including the R88DT turbine configurations), indicating the safety concern has broadened from initial targeted components to a more comprehensive regime covering fan, compressor, and turbine sections across all three engine series."},"complexity_factors":["Extensive tabular data with 40+ individual part entries across three engine sub-models (CF6-80A, CF6-80C2, CF6-80E1) plus R88DT turbine variants","Multiple inspection methods specified per part (fluorescent penetrant, magnetic particle, eddy current) with specific manual task numbers","Conditional logic for 'piece-part opportunity' definition requiring cumulative cycle counting and damage assessment","Cross-references to manufacturer engine manual chapters (72-XX-XX format) and FAA AD 2009-04-10","Asterisk notation system (* and **) to denote new parts versus updated inspection references","Variant-specific applicability (Pre SB 72-0150 vs Post SB, Configuration 1 vs Configuration 2, R88DT turbine configurations)","Dual compliance structure: administrative update (180 days) + recurring physical inspections (ongoing)"],"plain_english_summary":"CASA orders operators of aircraft with GE CF6‑80A/C2/E1 engines to revise maintenance programs and perform mandatory inspections of life‑limited rotating parts (fan, compressor, turbine components, seals) using fluorescent penetrant, magnetic particle or eddy‑current methods at piece‑part opportunities once parts have flown >100 cycles.\n\nThe measure targets airlines and maintenance providers to detect cracks before failure, preventing uncontained engine breakups that could damage aircraft or injure occupants."}},"importantCases":[],"_links":{"self":"/api/acts/ad-cf6-71-life-limited-parts","history":"/api/acts/ad-cf6-71-life-limited-parts/history","analysis":"/api/acts/ad-cf6-71-life-limited-parts/analysis","conflicts":"/api/acts/ad-cf6-71-life-limited-parts/conflicts","importantCases":"/api/acts/ad-cf6-71-life-limited-parts/important-cases","documents":"/api/acts/ad-cf6-71-life-limited-parts/documents"}}