AD 63-18-01
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Bombardier Inc. | CL-44D4 | Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft |
Unsafe Condition
Failure of an elevator hinge bolt.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Replace the elevator station 299 hinge bolt aluminum locking plate with steel components per Canadair Service Bulletin CL44D4-302. Replace aluminum locking plates at Stations 84, 174.9, and 181 with steel devices per CL44D4-316 Part A. Conduct inspections for damage on hinge components every 250 hours' time in service. Perform special inspections per Canadair Service Information Circulars based on stabilizer configuration.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 50 hours' time in service from the effective date of this AD for initial replacements. Subsequent actions have varying compliance times: 250 hours' time in service for other replacements and initial inspections, with some extendable to 500 hours with prior inspection. Inspections must recur every 250 hours' time in service from the last inspection.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Bombardier Inc. Model CL-44D4 aircraft as specified in Canadair Service Bulletins and Modification Summaries referenced in the AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Elevator Hinge Bolts
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_63-18-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 63-18-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft Subject: Elevator Hinge Bolts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/22/1963 Make: Bombardier Inc. Model: CL-44D4 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 63-18-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 63-18-01 SUBJECT HEADING: Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft ACTION: SUMMARY: DATES: Effective September 22, 1963. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 63-18-01 CANADAIR: Amdt. 608 Part 507 Federal Register August 22, 1963. Applies to all Model CL-44D4 aircraft. Compliance required as indicated. As a result of failure of an elevator hinge bolt the following must be accomplished: (a) Within 50 hours' time in service from the effective date of this AD, unless already accomplished, replace the elevator station 299 hinge bolt aluminum locking plate with both a steel locking plate and a steel hinge bolt retainer in accordance with Canadair Service Bulletin CL44D4-302 or FAA approved equivalent. (b) Within 250 hours' time in service from the effective date of this AD, unless already accomplished, replace the elevator hinge bolt aluminum locking plates at Stations 84, 174.9, and 181 with steel locking devices in accordance with Part A of Canadair Service Bulletin CL44D4-316, or FAA approved equivalent. Compliance time for incorporating this modification may be increased to 500 hours provided the hinges are inspected in accordance with (c) within 250 hours' time in service from the effective date of this AD. (c) Within 250 hours' time in service after installing the steel locking plate or device, and thereafter within 250 hours' time in service from the last inspection, inspect for damage the elevator hinge bolt head, bolt locking plate, and bolt retainer at Stations 84, 174.9, 181, and 299. Damaged parts must be replaced before further flight. (d) For aircraft incorporating horizontal stabilizers conforming to Canadair Modification Summary No. 44-502, or modified in accordance with Canadair Service Bulletin CL44D4-243, perform the special inspections of Canadair Service Information Circular No. 180- CL44D4, Issue No. 5, or subsequent FAA approved issues, within 250 hours' time in service from the effective date of this AD, and thereafter at the intervals noted in the Circular for particular inspections. (e) For aircraft incorporating horizontal stabilizers which do not conform to Canadair Modification Summary No. 44-502, or which have not been modified in accordance with Canadair Service Bulletin No. CL-44D4-248 accomplish the following: (1) Perform the special inspections of Canadair Service Information Circular No. 60-CL44D4, Issue 6, or subsequent FAA approved issues, at the intervals noted therein for particular inspections. Part (a) of Circular No. 60-CL44D4 must be initially performed within 35 hours' time in service from the effective date of this AD and Part (b) must be initially performed within 250 hours' time in service from the effective date of this AD. (2) Inspect for damage all elevator hinge support structure and attachment fittings on the rear face of the horizontal stabilizer rear spar at Stations 84, 174.9, 181, and 299, within 250 hours' time in service from the effective date of this AD and thereafter within 250 hours from last inspection. Damaged parts must either be replaced or repaired in accordance with an FAA approved repair procedure before further flight. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, International Engineering and Manufacturing Branch, International Division, Washington 25, D.C., may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This directive effective September 22, 1963. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_63-18-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 63-18-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft Subject: Elevator Hinge Bolts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 09/22/1963 Make: Bombardier Inc. Model: CL-44D4 Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 63-18-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: AD NUMBER: 63-18-01 SUBJECT HEADING: Airworthiness Directives; CANADAIR Model CL-44D4 Aircraft ACTION: SUMMARY: DATES: Effective September 22, 1963. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 63-18-01 CANADAIR: Amdt. 608 Part 507 Federal Register August 22, 1963. Applies to all Model CL-44D4 aircraft. Compliance required as indicated. As a result of failure of an elevator hinge bolt the following must be accomplished: (a) Within 50 hours' time in service from the effective date of this AD, unless already accomplished, replace the elevator station 299 hinge bolt aluminum locking plate with both a steel locking plate and a steel hinge bolt retainer in accordance with Canadair Service Bulletin CL44D4-302 or FAA approved equivalent. (b) Within 250 hours' time in service from the effective date of this AD, unless already accomplished, replace the elevator hinge bolt aluminum locking plates at Stations 84, 174.9, and 181 with steel locking devices in accordance with Part A of Canadair Service Bulletin CL44D4-316, or FAA approved equivalent. Compliance time for incorporating this modification may be increased to 500 hours provided the hinges are inspected in accordance with (c) within 250 hours' time in service from the effective date of this AD. (c) Within 250 hours' time in service after installing the steel locking plate or device, and thereafter within 250 hours' time in service from the last inspection, inspect for damage the elevator hinge bolt head, bolt locking plate, and bolt retainer at Stations 84, 174.9, 181, and 299. Damaged parts must be replaced before further flight. (d) For aircraft incorporating horizontal stabilizers conforming to Canadair Modification Summary No. 44-502, or modified in accordance with Canadair Service Bulletin CL44D4-243, perform the special inspections of Canadair Service Information Circular No. 180- CL44D4, Issue No. 5, or subsequent FAA approved issues, within 250 hours' time in service from the effective date of this AD, and thereafter at the intervals noted in the Circular for particular inspections. (e) For aircraft incorporating horizontal stabilizers which do not conform to Canadair Modification Summary No. 44-502, or which have not been modified in accordance with Canadair Service Bulletin No. CL-44D4-248 accomplish the following: (1) Perform the special inspections of Canadair Service Information Circular No. 60-CL44D4, Issue 6, or subsequent FAA approved issues, at the intervals noted therein for particular inspections. Part (a) of Circular No. 60-CL44D4 must be initially performed within 35 hours' time in service from the effective date of this AD and Part (b) must be initially performed within 250 hours' time in service from the effective date of this AD. (2) Inspect for damage all elevator hinge support structure and attachment fittings on the rear face of the horizontal stabilizer rear spar at Stations 84, 174.9, 181, and 299, within 250 hours' time in service from the effective date of this AD and thereafter within 250 hours from last inspection. Damaged parts must either be replaced or repaired in accordance with an FAA approved repair procedure before further flight. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, International Engineering and Manufacturing Branch, International Division, Washington 25, D.C., may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This directive effective September 22, 1963. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.