AD 87-04-01

AD Final Rules - DRS_87-04-01.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
87-04-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Piper Model PA-46-310P Airplanes
Subject:
Air Valve Linkage
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
02/19/1987
Effective Date:
02/24/1987
Make:
Piper Aircraft Inc.
Model:
PA-46-310P
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Superseded AD: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Superseded By: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: 87-04-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5558

AD NUMBER:   87-04-01

SUBJECT HEADING:   Airworthiness Directives; Piper Model PA-46-310P Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective February 24, 1987.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
87-04-01 PIPER: Amendment 39-5558. Applies to Model PA-46-310P (Serial Numbers 46-8408001 through 46-8608067, 4608001 through 4608018, 4608021, 4608023 and 4608025) airplanes certificated in any category.

Compliance: Required within the next 25 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished.

To prevent engine power loss, accomplish the following:

(a) Remove the top and the lower left-hand engine cowl.

(b) Determine whether or not the alternate air valve linkage shown in Figure 1. has been installed on the left side of the engine air box.

(1) If the alternate air valve linkage shown in Figure 1. is not installed, install the Alternate Air Valve Modification Kit offered in Piper Service Letter 985 dated April 18, 1986, in accordance with the instructions contained within the kit, and verify proper operation in accordance with the instructions in paragraphs (b)(2)(i) through (b)(2)(vii) below.

(2) If the alternate air valve linkage shown in Figure 1. is installed, accomplish the following unless already accomplished in accordance with Piper Service Bulletin 852 dated November 14, 1986:

(i) Position the alternate air control (located inside the cockpit) approximately mid-way between the primary and the alternate position.

(ii) Refer to Figure 1. and bend the stop tab so that the linkage is stopped 0.12 inch plus 0.060 minus 0.000 inch before center. This dimension is determined by measuring the perpendicular distance between a line through the centers of the cable lever and the valve lever hinge bolts and the center point of the center hinge bolt.

(iii) Position the alternate air control (located inside the cockpit) in the primary (up position). Insure that the control is in the gate that prevents it from springing downward.

(iv) Adjust the cable housing in the cable clamp so that the cable pushes the linkage against the stop tab.

(v) Resecure the cable clamp as necessary.

(vi) Operate the alternate air control (located inside the cockpit) between the primary and the alternate air positions.

(vii) Check for normal operation and that the linkage does not go over-center when the alternate air control (located inside the cockpit) is in the "primary position."

(c) Reinstall the lower left-hand and the top engine cowl.

(d) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

(e) An equivalent means of compliance with the requirements of this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia 30349.

All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Piper Aircraft Corporation, 2926 Piper Drive, Vero Beach, Florida 30960; or may examine the document(s) at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment becomes effective on February 24, 1987.



FIGURE 1
AD 87-04-01


FOOTER: