Airworthiness Directives; Piper Models PA 28-140, PA 28-150, PA-28-160, PA-28-180, PA-28-235, PA 32-260, and PA-32-300 Airplanes
Piper PA-28 Cherokee 140 · Airworthiness Directives
Overview
This document is an Airworthiness Directive (AD) issued by the Federal Aviation Administration (FAA) that applies to several Piper aircraft models, specifically the PA-28-140, among others. The directive mandates compliance for certain maintenance procedures related to the main landing gear torque links. The AD is effective from April 14, 1972, and outlines specific inspection and replacement requirements to ensure the safety and airworthiness of the affected aircraft. It is crucial for operators and maintenance personnel to adhere to the compliance timelines and procedures detailed in the directive to maintain the aircraft's operational safety.
- Effective date of the AD is April 14, 1972.
- Compliance required within 50 hours of torque link time or before 750 hours, whichever is later.
- Repetitive inspections must occur at intervals not exceeding 500 hours of torque link time.
- Inspect for cracks using visual or approved methods, including dye penetrant inspection.
- If cracks are found, replace the torque links before further flight.
Document
Source
Originally published by www.spookmate.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Airworthiness Directives
- Year
- 1972
- Pages
- 2
- File size
- 29 KB
- Publisher
- www.spookmate.com
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In this document
Compliance Requirements
Operators of the affected Piper models must comply with the AD within the next 50 hours of torque link time in service from the effective date, or before reaching 750 hours of torque link time, whichever comes later. Repetitive inspections are mandated at intervals not exceeding 500 hours of torque link time since the last inspection.
Inspection Procedures
To inspect the main landing gear torque links, operators must first remove paint at least one inch away from the machined boss. The area should be cleaned and dried, followed by a thorough inspection for cracks using visual methods or approved inspection techniques such as fluorescent or dye penetrant inspection.
Crack Detection and Action
If any cracks are detected during inspection, the affected torque links must be replaced with serviceable parts of the same part number before further flight. However, the aircraft may be flown to a maintenance base under specific conditions outlined in FAR 21.197.
Record Keeping
Operators who do not maintain records of individual torque link hours must use the total airplane hours in service for compliance purposes. Previous ADs related to the main landing gear torque links remain applicable.
Safety notes
- Operators must ensure compliance with the AD to maintain aircraft safety.
- Failure to inspect and replace defective torque links can lead to serious safety issues.
Full document text
DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Amendment 39-1433; AD 72-08-06 Airworthiness Directives; Piper Models PA 28-140, PA 28-150, PA-28-160, PA-28-180, PA-28-235, PA 32-260, and PA-32-300 Airplanes DATES: Effective April 14, 1972. 72-08-06 PIPER: Amendment 39-1433. Applies to Model PA 28-140 airplanes, Serial Numbers 28- 20000 and up; Model PA 28-150/-160/-180 airplanes, Serial Numbers 28-01 and up; Model PA 28-235 airplanes, Serial Numbers 28-10000 and up; Model PA 32-260 airplanes, Serial Numbers 32-01 and up; and Model PA 32-300 airplanes, Serial Numbers 32-40000 and up. Serial Numbers prefixed by model year, such as 28-7120000 are included in effectivity. For airplanes having main landing gear torque links, P/N 65691-00 or P/N 65691-00V, compliance required within the next 50 hours of torque link time in service from the effective date of this AD, or before the accumulation of 750 hours of torque link time in service, whichever occurs later, unless already accomplished in the last 450 hours of torque link time in service. Repetitive inspections are required at intervals not to exceed 500 hours of torque link time in service from last inspection. To detect cracks adjacent to the 2 1/2" diameter machined boss in any of the four main landing gear torque links (Piper Part No. 65691-00 or 65691-00V) accomplish the following: (a) Remove paint at least one inch away from the large boss by any suitable means which does not leave a wax residue. (b) Clean this area for inspection and allow to dry if necessary. (c) Inspect for cracks by any of the following methods: (1) Visually with the aid of at least a 10 power magnifying glass. (2) Fluorescent or dye penetrant inspection. (3) FAA approved equivalent inspection. (d) If cracks are present, replace the torque links with serviceable torque links of the same part number before further flight, except that the airplane may be flown in accordance with FAR 21.197 to a base where installation can be performed. Piper Service Letter No. 600 pertains to this same subject; however, compliance times must be in accordance with the provisions of this AD. Operators who have not kept records of hours time in service on individual torque links shall substitute airplane hours time in service in lieu thereof. Previous AD's 67-20-04 and 70-18-05, concerning main landing gear torque links are still applicable. Piper Kit No. 757-123 as mentioned in these AD's contains appropriate hardware for torque link installation and may be reused. This amendment becomes effective April 14, 1972.
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