AD 95-26-13 Airworthiness Directives; The New Piper Aircraft, Inc. (Formerly Piper Aircraft Corporation) PA28 and PA32 Series Airplanes

Makes named: piper. Read the applicability below — it usually turns on serial or part numbers too.

The following airplane models (all serial numbers), certificated in any category, that are equipped with oil cooler hose assemblies that do not meet TSO-C53a, Type D requirements: PA28-140 PA28-180 PA28R-201 PA28-235 PA32S-300 PA32R-301(SP) PA32-301T PA28-150 PA28S-180 PA28-151 PA28-236 PA32-301 PA32R-301(HP) PA28-160 PA28R-180 PA28-161 PA32-260 PA32R-300 PA32RT-300T PA28S-160 PA28R-200 PA28-181 PA32-300 PA32RT-300 PA32R-301T Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated in the body of this AD, unless already accomplished. To prevent oil cooler hoses from failing or rupturing, which could result in engine stoppage and subsequent loss of control of the airplane, accomplish the following: (a) Within the next 100 hours time-in-service (TIS) after the effective date of this AD, and thereafter at intervals not to exceed 100 hours TIS, inspect the oil cooler hoses to ensure that the hoses meet the criteria presented in the paragraphs below. (1) For airplanes that have any oil cooler hose assembly mounted at the front or back of the airplane, or both, the fire sleeve of the hose should not be soaked with oil or have a brownish or whitish color, and there should be no evidence of deterioration as a result of heat, brittleness, or oil seepage. Prior to further flight, replace any hose that is soaked with oil, has a brownish or whitish color, or has evidence of deterioration. (2) On airplanes that have any oil cooler hose assembly mounted in the front of the airplane, ensure that the following exists, and, prior to further flight, adjust accordingly: (i) The hose passes underneath and behind the electrical ground cable and in front of the lower of the two engine mount struts when the hose is routed to the rear of the engine; and (ii) The hose is tied to the engine mount strut and a clearance of at least 2 inches exists between the oil hose and exhaust stack. Note 2: Figure 1 of this AD relates to the conditions specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. BILLING CODE 4910-13-U [[Page 67324]] [GRAPHIC][TIFF OMITTED]TR29DE95.010 BILLING CODE 4910-13-C [[Page 67325]] (b) Upon the accumulation of 8 years or 1,000 hours TIS after installation of each oil cooler assembly, whichever occurs first, and thereafter every 8 years or 1,000 hours TIS (whichever occurs first), accomplish one of the following: (1) Replace each oil cooler hose assembly with a part number specified in the APPLICABILITY section of this AD, and reinspect in accordance with paragraph (a) of this AD at intervals not to exceed 100 hours TIS; or (2) Replace each oil cooler hose assembly with an approved TSO- C53a, Type D, hose assembly ensuring that there is a minimum of 2 inches between the oil cooler hoses and exhaust stacks (as applicable) upon installation. Ensure that there is a minimum bend radius of 6.5 inches on oil cooler assemblies incorporating 0.75- inch outer diameter hoses. (c) The replacement specified in paragraph (b)(2) of this AD may be accomplished at any time prior to the 8-year or 1,000-hour compliance time as terminating action for the 100-hour TIS repetitive inspection requirement of this AD. (d) After adjusting or installing oil cooler hoses, prior to further flight, run the engine for 5 minutes to ensure that there are no oil leaks and that the 2-inch clearance is maintained (as applicable) when the engine is warm. Prior to further flight, replace any leaking oil cooler hoses and adjust the clearance accordingly. Note 3: Although not required by this AD, the FAA recommends that an oil cooler hose flexibility test be accomplished at each 100-hour TIS inspection interval. Oil cooler hose flexibility may be determined by gently lifting the hose in several places from the bottom of its downward arc to the oil cooler. If the oil cooler hose moves slightly either from side-to-side or upward with the hand at the center of an even arc, then some flexibility remains. If the oil cooler hose appears hardened or inflexible, replacement is recommended. (e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office (ACO), Campus Building, 1701 Columbia Avenue, suite 2-160, College Park, Georgia 30337-2748. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. Note 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. Note 5: Alternative methods of compliance approved in accordance with AD 76-25-06 (superseded by this action) are not considered approved as alternative methods of compliance with this AD. (g) Figure 1 of this AD may be obtained from the Atlanta ACO at the address specified in paragraph (f) of this AD. This document or any other information that relates to this AD may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri. (h) This amendment (39-9472) supersedes AD 76-25-06, Amendment 39-2788. (i) This amendment (39-9472) becomes effective on February 5, 1996. Issued in Kansas City, Missouri, on December 19, 1995. Dwight A. Young, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 95-31351 Filed 12-28-95; 8:45 am] BILLING CODE 4910-13-U