AD 74-17-04
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-14 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-12 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-12S | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-15 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-16 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-16S | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-17 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-20 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-20-115 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-20-135 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-20S | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-20S-115 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-20S-135 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-22 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-22-108 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-22-135 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-22-150 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-22-160 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-22S-135 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-22S-150 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
| aircraft | FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. | PA-22S-160 | Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes |
Unsafe Condition
Sudden failure of the fabric at the top of the windshield where the fabric attaches to the channel.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Install Piper Kits 760 799 or 754 404 within 25 hours in service after the effective date if fabric exceeds three years since installation. Inspect fabric every 100 hours in service after initial kit installation, and add a fabric reinforcement strip if cracks or fraying are found. For airplanes with recent fabric installation, inspect every 100 hours until three years are accumulated, and install kits if issues are detected.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within the next 25 hours in service after the effective date of this AD on airplanes which have fabric exceeding three years since installation
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Piper Models PA-12 (Serial Numbers 12-2904 and higher, except specified exceptions), PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 (Serial Numbers 22-1 and up) airplanes certificated in all categories, covered with cotton or linen at the critical area on top of the windshield.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
Fabric Reinforcement
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_74-17-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 74-17-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes Subject: Fabric Reinforcement Status: Current Citation: This information is not available. Citation Publish Date: 04/07/1977 Effective Date: 04/11/1977 Make: FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. Model: PA-14 | PA-12 | PA-12S | PA-15 | PA-16 | PA-16S | PA-17 | PA-20 | PA-20-115 | PA-20-135 | PA-20S | P...Show more 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: This AD also supersedes 59-16-03. AIRWORTHINESS DIRECTIVES FINAL RULES: 74-17-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2865 AD NUMBER: 74-17-04 SUBJECT HEADING: Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes ACTION: SUMMARY: DATES: Effective April 11, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 74-17-04 PIPER: Amendment 39-1919 as amended by Amendment 39-2154 is further amended by Amendment 39-2865. Applies to the following Models which are covered with cotton or linen at the critical area on top of the windshield where the fabric attaches to the channel: PA-12, Serial Numbers 12-2904 and higher, except 12-2907, 12-2911, 12-2914, 12-2915, 12-2917, 12-2925, 12-2950, 12-3028-S and 12-3901 through 12-3903; PA-14; PA-15; PA-16; PA-17; PA-20; and PA-22 airplanes, Serial Numbers 22-1 and up, certificated in all categories. To prevent sudden failure of the fabric at the top of the windshield where the fabric attaches to the channel, accomplish the following: 1. For all airplanes, unless already accomplished, the indicated Piper Kits or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, must be installed within the next 25 hours in service after the effective date of this AD on airplanes which have fabric exceeding three years since installation: (a) Kit 760 799 effective on: PA-12, Serial numbers 12-2904 and higher, except 12-2907, 12-2911, 12-2914, 12-2915, 12-2917, 12-2925, 12-2950, 12-3028-S and 12-3901 through 12-3903; all PA-12S and PA-14 airplanes. (b) Kit 754 404 effective on: All PA-15, PA-16, PA-17 and PA-20 and PA-22 Airplane Serial Numbers 22-1 and up. 2. For all airplanes at every 100 hours in service after accomplishment of 1(a) or 1(b), remove the metallic strip and inspect the fabric over the top surface. (a) If no cracks or fraying are found, reinstall the metallic strip. (b) If any cracks or fraying are found, prior to further flight, add a fabric reinforcement strip (pinked-tape) starting from a line formed by the intersection of the windshield and the leading edge of the channel and extending aft at least three inches from the trailing edge of the channel. Reinstall the metallic strip. 3. For all airplanes which have fabric installed within the last three years, every 100 hours in service after the effective date of this AD, until three years are accumulated, inspect the fabric over the top surface. If any cracks or fraying are found, prior to further flight, install Piper Kits or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, as in 1(a) or 1(b) as appropriate. Upon request and appropriate substantiating data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Piper Service Letter No. 362A pertains to this subject. This AD supersedes AD 61-06-06. Amendment 39-1919 was effective August 16, 1974. Amendment 39-2154 was effective April 9, 1975. This amendment 39-2865 is effective April 11, 1977. FOOTER:
Document Text
Show stored source text (verify against official source)
AD Final Rules - DRS_74-17-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 74-17-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes Subject: Fabric Reinforcement Status: Current Citation: This information is not available. Citation Publish Date: 04/07/1977 Effective Date: 04/11/1977 Make: FS 2002 Corp. | FS 2003 Corp. | Piper Aircraft Inc. Model: PA-14 | PA-12 | PA-12S | PA-15 | PA-16 | PA-16S | PA-17 | PA-20 | PA-20-115 | PA-20-135 | PA-20S | P...Show more 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: This AD also supersedes 59-16-03. AIRWORTHINESS DIRECTIVES FINAL RULES: 74-17-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2865 AD NUMBER: 74-17-04 SUBJECT HEADING: Airworthiness Directives; Piper Models PA-12, PA-14, PA-15, PA-16, PA-17, PA-20, and PA-22 Airplanes ACTION: SUMMARY: DATES: Effective April 11, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 74-17-04 PIPER: Amendment 39-1919 as amended by Amendment 39-2154 is further amended by Amendment 39-2865. Applies to the following Models which are covered with cotton or linen at the critical area on top of the windshield where the fabric attaches to the channel: PA-12, Serial Numbers 12-2904 and higher, except 12-2907, 12-2911, 12-2914, 12-2915, 12-2917, 12-2925, 12-2950, 12-3028-S and 12-3901 through 12-3903; PA-14; PA-15; PA-16; PA-17; PA-20; and PA-22 airplanes, Serial Numbers 22-1 and up, certificated in all categories. To prevent sudden failure of the fabric at the top of the windshield where the fabric attaches to the channel, accomplish the following: 1. For all airplanes, unless already accomplished, the indicated Piper Kits or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, must be installed within the next 25 hours in service after the effective date of this AD on airplanes which have fabric exceeding three years since installation: (a) Kit 760 799 effective on: PA-12, Serial numbers 12-2904 and higher, except 12-2907, 12-2911, 12-2914, 12-2915, 12-2917, 12-2925, 12-2950, 12-3028-S and 12-3901 through 12-3903; all PA-12S and PA-14 airplanes. (b) Kit 754 404 effective on: All PA-15, PA-16, PA-17 and PA-20 and PA-22 Airplane Serial Numbers 22-1 and up. 2. For all airplanes at every 100 hours in service after accomplishment of 1(a) or 1(b), remove the metallic strip and inspect the fabric over the top surface. (a) If no cracks or fraying are found, reinstall the metallic strip. (b) If any cracks or fraying are found, prior to further flight, add a fabric reinforcement strip (pinked-tape) starting from a line formed by the intersection of the windshield and the leading edge of the channel and extending aft at least three inches from the trailing edge of the channel. Reinstall the metallic strip. 3. For all airplanes which have fabric installed within the last three years, every 100 hours in service after the effective date of this AD, until three years are accumulated, inspect the fabric over the top surface. If any cracks or fraying are found, prior to further flight, install Piper Kits or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, as in 1(a) or 1(b) as appropriate. Upon request and appropriate substantiating data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Piper Service Letter No. 362A pertains to this subject. This AD supersedes AD 61-06-06. Amendment 39-1919 was effective August 16, 1974. Amendment 39-2154 was effective April 9, 1975. This amendment 39-2865 is effective April 11, 1977. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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