AD 76-17-02

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AD Number:
76-17-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BEECH Models 58P and 58PA Airplanes
Subject:
Cabin Window
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/31/1978
Make:
Textron Aviation Inc.
Model:
58P | 58PA
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Superseded AD: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Superseded By: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: 76-17-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3324

AD NUMBER:   76-17-02

SUBJECT HEADING:   Airworthiness Directives; BEECH Models 58P and 58PA Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective October 31, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
76-17-02 BEECH: Amendment 39-2697 as amended by amendment 39-3324. Applies to Models 58P and 58PA (Serial Numbers TJ-2 through TJ-19, TJ-21 through TJ-45, TJ-47 through TJ-54, and TJ-56 through TJ-58) airplanes certificated in all categories.

Compliance: Required as indicated, unless already accomplished.

To prevent cracking of the cabin window located just forward of the cabin entrance door on the left side of the airplane, with resultant loss of cabin pressurization, accomplish the following:

A. On airplanes that do not have the window frame reinforcement installed, as defined in Beechcraft Service Instructions 0828-110, Revision I or later approved revisions, accomplish the following in accordance with said service instructions:

1. Within 25 hours' time in service after the effective date of this AD and at the two next 50 hour time in service intervals thereafter, visually inspect the cabin window just forward of the cabin door on the left side of the airplane for cracks and if cracks are found during any inspection required herein, prior to any flight during which the cabin is pressurized, replace the window and install the window frame reinforcement.

2. If no cracks have been found during any inspection required in Paragraph A.1., within 100 hours' time in service after the initial inspection required by Paragraph A.1. install the window frame reinforcement.

B. On airplanes that are flown unpressurized following discovery of a cracked window during any inspection required by Paragraph A of this Airworthiness Directive:

1. Fabricate a placard worded as follows: "DO NOT PRESSURIZE IN FLIGHT" and

2. Install said placard near the cabin pressurization control switch, and

3. Operate the aircraft in accordance with the placard until the cracked window is replaced.

C. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.

Amendment 39-2697 became effective August 24, 1976.

This amendment 39-3324 becomes effective October 31, 1978.

FOOTER: