AD 92-15-15

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AD Number:
92-15-15
Document Type:
AD Final Rules
Docket Number:
91-CE-97-AD
Subject Heading:
Airworthiness Directives; PIPER AIRCRAFT CORPORATION Model PA-36-300 and PA-36-375 Airplanes
Subject:
Engine Mount Attach Points
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
07/09/1992
Effective Date:
08/24/1992
Make:
Piper Aircraft Inc.
Model:
PA-36-300 | PA-36-375
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Superseded AD: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Superseded By: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: 92-15-15
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   91-CE-97-AD

AMENDMENT:   39-8309

AD NUMBER:   92-15-15

SUBJECT HEADING:   Airworthiness Directives; PIPER AIRCRAFT CORPORATION Model PA-36-300 and PA-36-375 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective August 24, 1992.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
92-15-15 PIPER AIRCRAFT CORPORATION: Amendment 39-8309. Docket No. 91-CE-97-AD.

Applicability: Model PA-36-300 airplanes (serial numbers 36-7760001 through 36-8160023) and Model PA-36-375 airplanes (serial numbers 36-7802001 through 36-8302025), certificated in any category.

Compliance: Required as indicated, unless already accomplished.

To prevent separation of the engine from the airplane because of cracks at the engine mount attach points, accomplish the following:

(a) Within the next 100 hours time-in-service (TIS) after the effective date of this AD, inspect the welds and areas adjacent to the welds at each engine mount attach point for cracks in accordance with the "INSTRUCTIONS: Inspection" section of Piper Service Bulletin (SB) No. 828, dated April 7, 1986.

(1) If cracks are found, prior to further flight, install gusset attachments in accordance with the "INSTRUCTIONS: Repair" section of Piper SB No. 828, dated April 7, 1986.

(2) If cracks are not found, reinstall the forward side panels and reinspect at intervals not to exceed 100 hours TIS.

NOTE 1: The compliance times referenced in this AD take precedence over those cited in the referenced service information.

(b) The installation described in paragraph (a)(1) of this AD may be accomplished at any time as terminating action for the repetitive inspections required by this AD.

(c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.

(d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office.

(e) The inspections and possible installation required by this AD shall be done in accordance with Piper Service Bulletin No. 828, dated April 7, 1986. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 32960. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC.

(f) This amendment becomes effective on August 24, 1992.

FOOTER: