AD 79-08-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Piper Aircraft Inc. | PA-38-112 | Airworthiness Directives; Piper Model PA-38-112 Aircraft |
Unsafe Condition
Crack in the stabilizer pulley bracket mounting fitting P/N 77615-07 or improperly torqued stabilizer to fin or fin to fuselage attaching bolts could cause possible hazards in flight.
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Required Actions
Inspect edges of stabilizer pulley bracket mounting fitting P/N 77615-07 for cracks using dye penetrant method. Report positive findings including crack length to FAA within ten days. Replace cracked fitting with undamaged part before further flight except ferry flight under FAR 21.197 may be approved. Check torque of stabilizer to fin and fin to fuselage bolts to 90-110 in-lbs using calibrated wrench and tighten as required.
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Compliance Time
within the next ten hours in service unless previously accomplished (for specified serial numbers in (a)) and within the next 100 hours in service unless previously accomplished (for serial numbers in (b))
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Affected Aircraft
Piper Model PA-38-112, Serial Nos. 38-78A0001 through 38-78A0040, 38-78A0042 through 38-78A0592, 38-78A0594, 38-78A0596, 38-78A0598 through 38-78A0620, 38-78A0622 through 38-78A0658, 38-78A0660 through 38-78A0714, 38-78A0716 through 38-78A0721, 38-78A0723 through 38-78A0735, 38-78A0737 through 38-78A0740, 38-78A0742, 38-78A0743, 38-78A0745 through 38-78A0766, 38-78A0768 through 38-78A0778, 38-78A0780 through 38-78A0784, 38-78A0787 through 38-78A0811, 38-78A0813, 38-78A0814, 38-78A0816, 38-78A0818, 38-78A0820, 38-78A0821, 38-78A0829, 38-78A0844, 38-79A0003 through 38-79A0005, 38-79A0007, 38-79A0008, 38-79A0010 through 38-79A0014, 38-79A0017 through 38-79A0030, 38-79A0033 through 38-79A0036, 38-79A0038 through 38-79A0041, 38-79A0043 through 38-79A0047, 38-79A0049 through 38-79A0078, 38-79A0080 through 38-79A0089, 38-79A0092, 38-79A0093, 38-79A0095, 38-79A0097 through 38-79A0099, 38-79A0101 through 38-79A0110, 38-79A0112 through 38-79A0114, 38-79A0116, 38-79A0119 through 38-79A0121, 38-79A0123 through 38-79A0128, 38-79A0130 through 38-79A0132, 38-79A0135 through 38-79A0137, 38-79A0139, 38-79A0140, 38-79A0142 through 38-79A0148, 38-79A0150 through 38-79A0165, 38-79A0167, 38-79A0168, 38-79A0170, 38-79A0172 through 38-79A0175, 38-79A0177, 38-79A0179 through 38-79A0181, 38-79A0184 through 38-79A0189, 38-79A0191 through 38-79A0197, 38-79A0199, 38-79A0200, 38-79A0204 through 38-79A0206, 38-79A0208 through 38-79A0212, 38-79A0214, 38-79A0216, 38-79A0217, 38-79A0220 through 38-79A0222, 38-79A0226, 38-79A0229 through 38-79A0231, 38-79A0234 through 38-79A0236, 38-79A0238, 38-79A0240, 38-79A0242, 38-79A0246, 38-79A0248, 38-79A0250, 38-79A0253, 38-79A0259, 38-79A0271 through 38-79A0273, 38-79A0277, 38-79A0301, 38-79A0307 and 38-79A0312 for part (a), and 38-78A0001 through 38-79A0254 for part (b).
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Stabilizer Bracket Fitting
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_79-08-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 79-08-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-38-112 Aircraft Subject: Stabilizer Bracket Fitting Status: Current Citation: This information is not available. Citation Publish Date: 04/12/1979 Effective Date: 04/12/1979 Make: Piper Aircraft Inc. Model: PA-38-112 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 79-08-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3446 AD NUMBER: 79-08-02 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-38-112 Aircraft ACTION: SUMMARY: DATES: Effective April 12, 1979. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 79-08-02 PIPER: Amendment 39-3446. Applies to Model PA-38-112, Serial Nos. as shown below, certificated in all categories. To avoid possible hazards in flight associated with a crack in the stabilizer pulley bracket mounting fitting P/N 77615-07 or improperly torqued stabilizer to fin or fin to fuselage attaching bolts, accomplish the following: (a) Serial Nos. 38-78A0001 through 38-78A0040, 38-78A0042 through 38-78A0592, 38-78A0594, 38-78A0596, 38-78A0598 through 38-78A0620, 38-78A0622 through 38-78A0658, 38-78A0660 through 38-78A0714, 38-78A0716 through 38-78A0721, 38-78A0723 through 38-78A0735, 38-78A0737 through 38-78A0740, 38-78A0742, 38-78A0743, 38-78A0745 through 38-78A0766, 38-78A0768 through 38-78A0778, 38-78A0780 through 38-78A0784, 38-78A0787 through 38-78A0811, 38-78A0813, 38-78A0814, 38-78A0816, 38-78A0818, 38-78A0820, 38-78A0821, 38-78A0829, 38-78A0844, 38-79A0003 through 38-79A0005, 38-79A0007, 38-79A0008, 38-79A0010 through 38-79A0014, 38-79A0017 through 38-79A0030, 38-79A0033 through 38-79A0036, 38-79A0038 through 38-79A0041, 38-79A0043 through 38-79A0047, 38-79A0049 through 38-79A0078, 38-79A0080 through 38-79A0089, 38-79A0092, 38-79A0093, 38-79A0095, 38-79A0097 through 38-79A0099, 38-79A0101 through 38-79A0110, 38-79A0112 through 38-79A0114, 38-79A0116, 38-79A0119 through 38-79A0121, 38-79A0123 through 38-79A0128, 38-79A0130 through 38-79A0132, 38-79A0135 through 38-79A0137, 38-79A0139, 38-79A0140, 38-79A0142 through 38-79A0148, 38-79A0150 through 38-79A0165, 38-79A0167, 38-79A0168, 38-79A0170, 38-79A0172 through 38-79A0175, 38-79A0177, 38-79A0179 through 38-79A0181, 38-79A0184 through 38-79A0189, 38-79A0191 through 38-79A0197, 38-79A0199, 38-79A0200, 38-79A0204 through 38-79A0206, 38-79A0208 through 38-79A0212, 38-79A0214, 38-79A0216, 38-79A0217, 38-79A0220 through 38-79A0222, 38-79A0226, 38-79A0229 through 38-79A0231, 38-79A0234 through 38-79A0236, 38-79A0238, 38-79A0240, 38-79A0242, 38-79A0246, 38-79A0248, 38-79A0250, 38-79A0253, 38-79A0259, 38-79A0271 through 38-79A0273, 38-79A0277, 38-79A0301, 38-79A0307 and 38-79A0312. Compliance required within the next ten hours in service unless previously accomplished. 1. Remove the dorsal fin forward fairing P/N 77606-03 and inspect the edges of the stabilizer pulley bracket mounting fitting P/N 77615-07 at the bend radius for cracks using a dye penetrant inspection method. 2. Report positive findings including crack length from paragraph (a) Inspection to Chief, Engineering and Manufacturing Branch, FAA, Eastern Region within ten days of inspection. (Reporting approved by Office of Management and Budget under OMB No. 04-RO174.) 3. If a cracked fitting is found, replace with an undamaged part of the same part number before further flight except a ferry flight under FAR 21.197 to a place of repair may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) Serial Nos. 38-78A0001 through 38-79A0254. Compliance required within the next 100 hours in service unless previously accomplished. 1. Disconnect rudder cables from rudder, remove lower rudder hinge bolt and displace rudder to gain access to rear spar attachment bolts. 2. Remove lower vertical fin fairing, upper vertical fin fairing, upper vertical fin inspection panel and lower aft vertical fin inspection panel. 3. Using a calibrated torque wrench, check the torque of each of eighteen (18) stabilizer to fin and fin to fuselage attach bolts and tighten as required to 90-110 in-lbs. Torque value given takes into account friction drag torque. (Piper Service Bulletin No. 637 refers to the subject.) This amendment is effective April 12, 1979. FOOTER:
Document Text
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AD Final Rules - DRS_79-08-02.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 79-08-02 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Model PA-38-112 Aircraft Subject: Stabilizer Bracket Fitting Status: Current Citation: This information is not available. Citation Publish Date: 04/12/1979 Effective Date: 04/12/1979 Make: Piper Aircraft Inc. Model: PA-38-112 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: AIR-700: Compliance & Airworthiness Division Office of Primary Responsibility: AIR-720: Operational Safety Branch CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 79-08-02 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-3446 AD NUMBER: 79-08-02 SUBJECT HEADING: Airworthiness Directives; Piper Model PA-38-112 Aircraft ACTION: SUMMARY: DATES: Effective April 12, 1979. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 79-08-02 PIPER: Amendment 39-3446. Applies to Model PA-38-112, Serial Nos. as shown below, certificated in all categories. To avoid possible hazards in flight associated with a crack in the stabilizer pulley bracket mounting fitting P/N 77615-07 or improperly torqued stabilizer to fin or fin to fuselage attaching bolts, accomplish the following: (a) Serial Nos. 38-78A0001 through 38-78A0040, 38-78A0042 through 38-78A0592, 38-78A0594, 38-78A0596, 38-78A0598 through 38-78A0620, 38-78A0622 through 38-78A0658, 38-78A0660 through 38-78A0714, 38-78A0716 through 38-78A0721, 38-78A0723 through 38-78A0735, 38-78A0737 through 38-78A0740, 38-78A0742, 38-78A0743, 38-78A0745 through 38-78A0766, 38-78A0768 through 38-78A0778, 38-78A0780 through 38-78A0784, 38-78A0787 through 38-78A0811, 38-78A0813, 38-78A0814, 38-78A0816, 38-78A0818, 38-78A0820, 38-78A0821, 38-78A0829, 38-78A0844, 38-79A0003 through 38-79A0005, 38-79A0007, 38-79A0008, 38-79A0010 through 38-79A0014, 38-79A0017 through 38-79A0030, 38-79A0033 through 38-79A0036, 38-79A0038 through 38-79A0041, 38-79A0043 through 38-79A0047, 38-79A0049 through 38-79A0078, 38-79A0080 through 38-79A0089, 38-79A0092, 38-79A0093, 38-79A0095, 38-79A0097 through 38-79A0099, 38-79A0101 through 38-79A0110, 38-79A0112 through 38-79A0114, 38-79A0116, 38-79A0119 through 38-79A0121, 38-79A0123 through 38-79A0128, 38-79A0130 through 38-79A0132, 38-79A0135 through 38-79A0137, 38-79A0139, 38-79A0140, 38-79A0142 through 38-79A0148, 38-79A0150 through 38-79A0165, 38-79A0167, 38-79A0168, 38-79A0170, 38-79A0172 through 38-79A0175, 38-79A0177, 38-79A0179 through 38-79A0181, 38-79A0184 through 38-79A0189, 38-79A0191 through 38-79A0197, 38-79A0199, 38-79A0200, 38-79A0204 through 38-79A0206, 38-79A0208 through 38-79A0212, 38-79A0214, 38-79A0216, 38-79A0217, 38-79A0220 through 38-79A0222, 38-79A0226, 38-79A0229 through 38-79A0231, 38-79A0234 through 38-79A0236, 38-79A0238, 38-79A0240, 38-79A0242, 38-79A0246, 38-79A0248, 38-79A0250, 38-79A0253, 38-79A0259, 38-79A0271 through 38-79A0273, 38-79A0277, 38-79A0301, 38-79A0307 and 38-79A0312. Compliance required within the next ten hours in service unless previously accomplished. 1. Remove the dorsal fin forward fairing P/N 77606-03 and inspect the edges of the stabilizer pulley bracket mounting fitting P/N 77615-07 at the bend radius for cracks using a dye penetrant inspection method. 2. Report positive findings including crack length from paragraph (a) Inspection to Chief, Engineering and Manufacturing Branch, FAA, Eastern Region within ten days of inspection. (Reporting approved by Office of Management and Budget under OMB No. 04-RO174.) 3. If a cracked fitting is found, replace with an undamaged part of the same part number before further flight except a ferry flight under FAR 21.197 to a place of repair may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (b) Serial Nos. 38-78A0001 through 38-79A0254. Compliance required within the next 100 hours in service unless previously accomplished. 1. Disconnect rudder cables from rudder, remove lower rudder hinge bolt and displace rudder to gain access to rear spar attachment bolts. 2. Remove lower vertical fin fairing, upper vertical fin fairing, upper vertical fin inspection panel and lower aft vertical fin inspection panel. 3. Using a calibrated torque wrench, check the torque of each of eighteen (18) stabilizer to fin and fin to fuselage attach bolts and tighten as required to 90-110 in-lbs. Torque value given takes into account friction drag torque. (Piper Service Bulletin No. 637 refers to the subject.) This amendment is effective April 12, 1979. FOOTER:
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