AD 77-22-01
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Textron Aviation Inc. | 65 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | 65-80 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | 65-88 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | 65-90 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | 65-A80 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | 65-A80-8800 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | 65-A90 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | 65-B80 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | 70 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | A65 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | A65-8200 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | B90 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | C90 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
| aircraft | Textron Aviation Inc. | E90 | Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes |
Unsafe Condition
Cracks in the fuselage station 380.00 bulkhead and attached components, and gaps exceeding 0.020 inches between the horizontal stabilizer aft spar and attach plates on the bulkhead, which could compromise structural integrity.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the fuselage station 380.00 bulkhead and components for cracks using light and mirror; measure gaps between spar and attach plates with feeler gauges; remove and inspect bolts for cracks; correct gaps exceeding 0.020 inches; file or grind bushings flush with spar; replace cracked components with specified part numbers; comply with service instructions and contact Beech Aircraft for further repair instructions if cracks are found.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 50 hours time in service after August 19, 1976, or upon accumulation of 650 hours time in service for aircraft with less than 600 hours on August 19, 1976, and at 600 hour intervals thereafter, or within the next 650 hours time in service after the AD's effective date if the next inspection under paragraph B is within less than 50 hours.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Beech Models 65, A65, A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 airplanes with specific serial ranges: Models 65, A65, A65-8200 (Serial Numbers L-1, L-2, L-6, LF-7, LF-8, LC-1 through LC-335); 65-80, 65-A80, 65-A80-8800, 65-B80 (LD-1 through LD-512); 65-88 (LP-1 through LP-26, LP-28, LP-30 through LP-47); 65-90, 65-A90, B90, C90 (LJ-1 through LJ-711); 70 (LB-1 through LB-35); E90 (LW-1 through LW-212).
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Fuselage Structure
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_77-22-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 77-22-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65...Show more Subject: Fuselage Structure Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/23/1978 Make: Textron Aviation Inc. Model: 65 | 65-80 | 65-88 | 65-90 | 65-A80 | 65-A80-8800 | 65-A90 | 65-B80 | 70 | A65 | A65-8200 | B90 | C9...Show more Product Type: Aircraft Product Subtype: Small 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: 77-22-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3280 AD NUMBER: 77-22-01 SUBJECT HEADING: Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes ACTION: SUMMARY: DATES: Effective August 23, 1978 ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 77-22-01 BEECH: Amendment 39-3066 as amended by Amendment 39-3280. Applies to Beech Models 65, A65 and A65-8200 (Serial Numbers L-1, L-2, L-6, LF-7, LF-8 and LC-1 through LC-335), 65-80, 65-A80, 65-A80-8800 and 65-B80 (Serial Numbers LD-1 through LD-512), 65-88 (Serial Numbers LP-1 through LP-26, LP-28 and LP-30 through LP-47), 65-90, 65- A90, B90 and C90 (Serial Numbers LJ-1 through LJ-711), 70 (Serial Numbers LB-1 through LB- 35) and E90 (Serial Numbers LW-1 through LW-212) airplanes certificated in all categories. Compliance: Required as indicated, unless already accomplished. To assure continued structural integrity of the fuselage to the horizontal tail rear spar attachment accomplish the following in accordance with Beechcraft Service Instructions No. 0755-103, Revision II or later approved revisions and in accordance with the additional requirements set forth below: A) Accomplish the following at the next bulkhead inspection required by paragraph "B" of this AD, except that if said paragraph "B" inspection is required in less than 50 hours time in service from the effective date of this AD, accomplish the following within the next 650 hours time in service after the effective date of this AD. NOTE: The intent of the compliance time shown for paragraph "A" is to require compliance at the first paragraph "B" bulkhead inspection that occurs between 50 and 650 hours time in service after the effective date of this AD. 1. Remove the tail cone. 2. Inspect the right and left horizontal stabilizers aft spar attachment to the fuselage station 380.00 bulkhead by loosening all 12 attach bolts and by using feeler gauges, measure the gap between the spar and the attach plates on the bulkhead at each bolt hole. Correct any gap exceeding .020 inches, by complying with instructions in the aforementioned Beechcraft Service Instructions. 3. Remove the aft spar attach bolts one at a time and, using a suitable feeler gauge, check for protrusion of the attach point bushing from the forward surface of the spar. If the forward face of the bushings is not flush with the front surface of the spar, complete removal of the stabilizer, and prior to reinstallation, correct by filing or grinding the bushings flush with the front surface of the spar. 4. Reinstall the stabilizers if removed. B) Within 50 hours time in service after August 19, 1976, for aircraft with 600 hours or more time in service on that date, or upon the accumulation of 650 hours time in service for aircraft having less than 600 hours time in service on August 19, 1976, or within 600 hours time in service after the last inspection in accordance with AD 76-16-04, and at 600 hour intervals thereafter, accomplish the following: 1. Remove the tail cone from the airplane. 2. Using a light and mirror, inspect the forward and aft side of the P/N 50- 440028-65 (F.S. 380.00) bulkhead and all of the bulkhead stiffeners, doublers and other components that attach to the bulkhead for cracks. Pay particular attention to the edges of these parts and the areas around their attaching rivets and bolts. 3. Remove right and left horizontal stabilizers aft spar attach bolts one at a time and inspect the contact areas under the bolt heads and nuts for cracks. 4. If no cracks are detected no further action is required until the next repetitive inspection required by this paragraph is due. 5. If cracks are found, proceed with paragraph C below. C) If cracks are found as a result of any inspection required by this AD, prior to further flight, contact Beech Aircraft Corporation, Commercial Services Operations, Wichita, Kansas 67201, for appropriate instructions and either repair (using acceptable methods, techniques and practices per Advisory Circular 43.13-1A) or replace any cracked P/N 50- 440028-65 fuselage station 380.00 bulkhead and replace any cracked attached stiffener, doubler or other components with new components having part numbers shown in the parts list for Figure 1 in the aforementioned Beechcraft Service Instructions. NOTE: If one or more of the four vertical stiffeners or the doubler defined in Figure 1 of the above-noted Beechcraft Service Instructions as index numbers 2, 10 and 13 require replacement, it is recommended that all four of the vertical stiffeners and the doubler be replaced at the same time with new improved components having the part numbers specified in Paragraph D of this AD. D) The repetitive inspections required by Paragraph "B" of this AD are no longer required after Paragraph "A" of this AD has been complied with and Beechcraft part number 50- 440028-69, -70, -77 and -78 stiffeners and 50-440028-79 doubler have been installed. E) Aircraft found to have the bulkhead or stiffeners cracked may be flown in accordance with FAR 21.197 to a base where the required repair or replacement can be accomplished. F) The time interval between the repetitive bulkhead and stiffener inspections required by Paragraph "B" of this AD, after their initial inspection, can be adjusted up to 50 hours time in service to a maximum interval of 650 hours to allow coordination of these inspections with regular scheduled maintenance. G) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-3066 superseded Amendment 39-2690 (41 F.R. 34583). AD 76-16-04. Amendment 39-3066 became effective November 3, 1977. This amendment 39-3280 becomes effective August 23, 1978. FOOTER:
Document Text
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AD Final Rules - DRS_77-22-01.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 77-22-01 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65...Show more Subject: Fuselage Structure Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 08/23/1978 Make: Textron Aviation Inc. Model: 65 | 65-80 | 65-88 | 65-90 | 65-A80 | 65-A80-8800 | 65-A90 | 65-B80 | 70 | A65 | A65-8200 | B90 | C9...Show more Product Type: Aircraft Product Subtype: Small 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: 77-22-01 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3280 AD NUMBER: 77-22-01 SUBJECT HEADING: Airworthiness Directives; BEECH Models 65, A65 and A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, 65-90, 65-A90, B90, C90, 70, and E90 Airplanes ACTION: SUMMARY: DATES: Effective August 23, 1978 ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 77-22-01 BEECH: Amendment 39-3066 as amended by Amendment 39-3280. Applies to Beech Models 65, A65 and A65-8200 (Serial Numbers L-1, L-2, L-6, LF-7, LF-8 and LC-1 through LC-335), 65-80, 65-A80, 65-A80-8800 and 65-B80 (Serial Numbers LD-1 through LD-512), 65-88 (Serial Numbers LP-1 through LP-26, LP-28 and LP-30 through LP-47), 65-90, 65- A90, B90 and C90 (Serial Numbers LJ-1 through LJ-711), 70 (Serial Numbers LB-1 through LB- 35) and E90 (Serial Numbers LW-1 through LW-212) airplanes certificated in all categories. Compliance: Required as indicated, unless already accomplished. To assure continued structural integrity of the fuselage to the horizontal tail rear spar attachment accomplish the following in accordance with Beechcraft Service Instructions No. 0755-103, Revision II or later approved revisions and in accordance with the additional requirements set forth below: A) Accomplish the following at the next bulkhead inspection required by paragraph "B" of this AD, except that if said paragraph "B" inspection is required in less than 50 hours time in service from the effective date of this AD, accomplish the following within the next 650 hours time in service after the effective date of this AD. NOTE: The intent of the compliance time shown for paragraph "A" is to require compliance at the first paragraph "B" bulkhead inspection that occurs between 50 and 650 hours time in service after the effective date of this AD. 1. Remove the tail cone. 2. Inspect the right and left horizontal stabilizers aft spar attachment to the fuselage station 380.00 bulkhead by loosening all 12 attach bolts and by using feeler gauges, measure the gap between the spar and the attach plates on the bulkhead at each bolt hole. Correct any gap exceeding .020 inches, by complying with instructions in the aforementioned Beechcraft Service Instructions. 3. Remove the aft spar attach bolts one at a time and, using a suitable feeler gauge, check for protrusion of the attach point bushing from the forward surface of the spar. If the forward face of the bushings is not flush with the front surface of the spar, complete removal of the stabilizer, and prior to reinstallation, correct by filing or grinding the bushings flush with the front surface of the spar. 4. Reinstall the stabilizers if removed. B) Within 50 hours time in service after August 19, 1976, for aircraft with 600 hours or more time in service on that date, or upon the accumulation of 650 hours time in service for aircraft having less than 600 hours time in service on August 19, 1976, or within 600 hours time in service after the last inspection in accordance with AD 76-16-04, and at 600 hour intervals thereafter, accomplish the following: 1. Remove the tail cone from the airplane. 2. Using a light and mirror, inspect the forward and aft side of the P/N 50- 440028-65 (F.S. 380.00) bulkhead and all of the bulkhead stiffeners, doublers and other components that attach to the bulkhead for cracks. Pay particular attention to the edges of these parts and the areas around their attaching rivets and bolts. 3. Remove right and left horizontal stabilizers aft spar attach bolts one at a time and inspect the contact areas under the bolt heads and nuts for cracks. 4. If no cracks are detected no further action is required until the next repetitive inspection required by this paragraph is due. 5. If cracks are found, proceed with paragraph C below. C) If cracks are found as a result of any inspection required by this AD, prior to further flight, contact Beech Aircraft Corporation, Commercial Services Operations, Wichita, Kansas 67201, for appropriate instructions and either repair (using acceptable methods, techniques and practices per Advisory Circular 43.13-1A) or replace any cracked P/N 50- 440028-65 fuselage station 380.00 bulkhead and replace any cracked attached stiffener, doubler or other components with new components having part numbers shown in the parts list for Figure 1 in the aforementioned Beechcraft Service Instructions. NOTE: If one or more of the four vertical stiffeners or the doubler defined in Figure 1 of the above-noted Beechcraft Service Instructions as index numbers 2, 10 and 13 require replacement, it is recommended that all four of the vertical stiffeners and the doubler be replaced at the same time with new improved components having the part numbers specified in Paragraph D of this AD. D) The repetitive inspections required by Paragraph "B" of this AD are no longer required after Paragraph "A" of this AD has been complied with and Beechcraft part number 50- 440028-69, -70, -77 and -78 stiffeners and 50-440028-79 doubler have been installed. E) Aircraft found to have the bulkhead or stiffeners cracked may be flown in accordance with FAR 21.197 to a base where the required repair or replacement can be accomplished. F) The time interval between the repetitive bulkhead and stiffener inspections required by Paragraph "B" of this AD, after their initial inspection, can be adjusted up to 50 hours time in service to a maximum interval of 650 hours to allow coordination of these inspections with regular scheduled maintenance. G) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-3066 superseded Amendment 39-2690 (41 F.R. 34583). AD 76-16-04. Amendment 39-3066 became effective November 3, 1977. This amendment 39-3280 becomes effective August 23, 1978. FOOTER:
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