AD 86-13-01

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AD Number:
86-13-01
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Wytwornia Model PZL M18 Series Airplanes
Subject:
Check for Cracks
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/19/1986
Make:
Polskie Zaklady Lotnieze Spolka zo.o
Model:
PZL M18
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 86-13-01
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5330

AD NUMBER:   86-13-01

SUBJECT HEADING:   Airworthiness Directives; Wytwornia Model PZL M18 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 19, 1986.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
86-13-01 WYTWORNIA SPRZETU KOMUNIKACYJNEGO: Amendment 39-5330. Applies to Model(s) PZL M18 (S/Ns up to and including 1Z012-40) airplanes, certificated in any category.

Compliance: Required as indicated after the effective date of this AD, unless already accomplished.

To prevent loss of engine control, accomplish the following:

(a) Before the first flight of each day:

(1) Visually check the following parts for the absence of discernible deformation, corrugation and cracks in accordance with Wytwornia Sprzetu Komunikacyjnego, PZL-Mielec Mandatory Service Bulletin (MSB) No. E/02.064/84, dated April 1984:

(i) The propeller pitch control system load carrying tube, P/N D65.250.00.2 (see the above S/B Sketch No. 1, sheet 1).

(ii) The propeller pitch control system bracket, P/N D65.012.00.1 (see the above S/B Sketch No. 1, sheet 1).

(iii) The throttle control system torque tube, P/N D65.210.00.1 (see the above S/B Sketch No. 1, sheet 2).

(iv) The engine mounting frame struts (see the above S/B Sketch No. 2).

(2) If no cracks, deformations, or corrugations are found, record compliance with paragraph (a)(1) of this AD in the aircraft maintenance records in accordance with FAR 91.173.

(3) If any crack, deformation, or corrugation is found, replace the damaged part before the next flight as follows:

(i) The propeller pitch control tube with a new serviceable part, or accomplish (iv).

(ii) The propeller pitch control bracket with a new serviceable part, or accomplish (iv).

(iii) The throttle control torque tube with a new serviceable part or an improved part in accordance with Mandatory Design Bulletin (MDB) No. K/02.067/84, dated July 1984, or accomplish (iv).

(iv) The torque tube system with either the D65.300.00.4 propeller pitch control cable installation and the D65.310.00.4 throttle control cable installation in accordance with MDB No. K/02.060/83 dated October 1983, or alternatively replace both with the 56-3632-0062 cable installations in accordance with Mandatory Engineering Bulletin (MEB) No. K/02.070/84.

(v) The engine frame struts with new serviceable units or with an improved engine mount P/N D64.100.00.5 in accordance with MDB No. K/02.060/83, dated October 1983.

(b) The daily visual check required by paragraph (a)(1) of this AD may be performed by the holder of a pilot certificate issued under FAR Part 61 on any airplane which is not used for operations under FAR Part 121, 127, 129, or 135.

(c) Within 50 hours time-in-service (TIS) after the effective date of this AD and every 50 hours TIS thereafter:

(1) Visually inspect for cracks, using a 5X power (or greater) magnifying glass, the parts described in paragraphs (a)(1)(i) through (a)(1)(iv) of this AD in accordance with MSB E/02.064/84.

(2) If any crack is found, prior to the next flight accomplish the corrective action described in paragraph (a)(3) of this AD.

(d) The intervals between the repetitive 50 hour TIS inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishment of these inspections concurrent with other scheduled maintenance of the airplane.

(e) Aircraft may be flown in accordance with FAR 21.197 to a location where paragraph (a)(3) and (c) of this AD can be accomplished.

(f) The daily and 50 hour TIS repetitive inspections specified by this AD are no longer required after MDB No. K/02.060/83, dated October 1983, is accomplished. If MEB No. K/02.070/84 is accomplished prior to MDB No. K/02.060/83, the inspections specified by this AD on the propeller and throttle controls are no longer required. The engine frame inspection would still be required.

(g) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium.

All persons affected by this directive may obtain copies of the documents referred to herein upon request to Wytwornia Sprzetu Komunikacyjnego, PZL-Mielec, 39-301 Mielec, Poland, or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This amendment becomes effective on July 19, 1986.

FOOTER: