AD 76-14-08

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AD Number:
76-14-08
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; CESSNA Model 177B and Model 177RG airplanes
Subject:
Horizontal Stabilator Trim Tab Actuator
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/22/1976
Make:
Cessna Aircraft Company
Model:
177B | 177RG
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Superseded AD: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Superseded By: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: 76-14-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2671

AD NUMBER:   76-14-08

SUBJECT HEADING:  
Airworthiness Directives; CESSNA Model 177B and Model 177RG airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 22, 1976.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
76-14-08 CESSNA: Amendment 39-2671. Applies to Model 177B (Serial Numbers 17702255 through 17702484, 17702486, 17702489, 17702492 and 17702494) and Model 177RG (Serial Numbers 177RG0700 through 177RG0883, 177RG0885 through 177RG0916, 177RG0919, 177RG0920, 177RG0922, 177RG0923, 177RG0925 through 177RG0928, 177RG0930, 177RG0933, 177RG0935 and 177RG0937) airplanes.

Compliance: Required as indicated, unless already accomplished.

To assure proper attachment of the stabilator trim tab actuator to the trim tab linkage, accomplish the following prior to next flight:

A. Remove round access panels located near the stabilator leading edge on the right and left side of the aircraft to gain access to the horizontal stabilator trim tab actuator.

B. 1. Visually inspect the -27 bolt which attaches the P/N 1260074-5 stabilator trim tab actuator to the P/N 1712142-1 bellcrank (refer to Figure 1) to determine if there is a nut installed on the end of the bolt.

NOTE: The -27 bolt must have a head on one end and a nut on the other end (refer to Figure 1).


FIGURE 1
AD 76-14-08

2. If the -27 bolt has a nut installed (castellated nut with a cotter pin or a self-locking nut) and the nut is not loose, reinstall the access panels and accomplish Paragraph C below.

NOTE: Except for those aircraft utilized in air carrier service, Paragraphs A, B.1., B.2. and C. may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any aircraft owned and operated by that person.

3. If the nut is loose or missing a certificated mechanic or certificated agency must install an AN3-6 bolt, AN960-10 washer, AN310-3 nut and MS24665-134 cotter pin in accordance with data in applicable Cessna maintenance manuals; reinstall the access panels; and accomplish Paragraphs C and D.

C. Make an entry in the permanent maintenance records to be retained and transferred with the aircraft which includes: Identification of the AD, method of compliance, date of compliance, and name, signature and certificate number of the pilot and/or mechanic or agency accomplishing the AD.

D. Within 48 hours after compliance with Paragraph B.3., notify in writing the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Federal Building, 601 East 12th Street, Kansas City, Missouri 64106, of any missing or loose nuts, aircraft serial number, total aircraft time in service and date of last annual or 100-hour inspection on the airplane. (Reporting approved by the Office of Management and Budget under OMB No. 04-RO174.)

E. Any alternate means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.

Cessna Service Letter No. SE76-14 or later approved revisions covers the subject matter of this AD.

This amendment becomes effective July 22, 1976, to all persons except those to whom it was made effective earlier by air mail letters issued June 28, 1976.


FOOTER: