AD 84-24-53 R1

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AD Number:
84-24-53 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; EMBRAER Models EMB-110P1 and EMB-110P2 Airplanes
Subject:
Empennage Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/17/1985
Make:
Embraer S.A.
Model:
EMB-110P1 | EMB-110P2
Product Type:
Aircraft
Product Subtype:
Small/Large 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Superseded AD: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Superseded By: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: 84-24-53 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4975

AD NUMBER:   84-24-53 R1

SUBJECT HEADING:   Airworthiness Directives; EMBRAER Models EMB-110P1 and EMB-110P2 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective January 17, 1985.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
84-24-53 R1 EMBRAER: Amendment 39-4975. Applies to Models EMB-110P1 and EMB- 110P2 airplanes certificated in any category.

Compliance: Required within the next ten (10) hours time-in-service, unless previously accomplished within the last fifty (50) hours time-in-service.

To preclude possible structural failure of the empennage assembly, accomplish the following:

(a) Unless the structural reinforcements and rivet replacements specified in paragraphs (d) and (e) of AD 83-14-09 (Amendment 39-4692) have already been accomplished, repeat the inspections of the horizontal stabilizer front attachment and fuselage bulkhead 33 area in accordance with paragraph (a) of AD 83-14-09.

(b) If loose rivets or cracks of any length are found during the inspections required by paragraph (a), prior to further flight, replace the rivets in accordance with paragraph (b) of AD 83- 14-09 and repair the cracks in accordance with paragraph (c)(2) of AD 83-14-09 notwithstanding the three inch crack criteria of that paragraph.

(c) Visually inspect the following components for loose attachments, excessive wear, corrosion, cracks and structural deformation:

(1) Forward horizontal stabilizer attachment, including the fuselage and stabilizer attach fittings and attachment hardware.

(2) Aft horizontal stabilizer attachment, including the fuselage and stabilizer attach fittings, attach links and all attachment hardware.

(3) All elevator to stabilizer hinge fittings, including all bearings/bushings and attachment hardware.

(4) Security of elevator mass balance weight assemblies.

(5) Left and right elevator Bellcrank assemblies and attachment hardware.

(6) Left and right elevator torque tube assemblies and all attachment hardware.

(7) Elevator trim tab hinges.

(8) Elevator trim tab actuator, bearings, push rod assembly and all attachment hardware.

(9) Elevator trim tab free play, measured at the trailing edge, should not exceed airplane
maintenance manual limits.

(d) Prior to further flight, correct any unsatisfactory conditions found as a result of the inspections required by paragraph (c) in accordance with the airplane maintenance manual.

(e) Report any unsatisfactory conditions, within 24 hours, to the FAA, Airframe Branch, Atlanta Aircraft Certification Office; Telephone (404) 763-7407. (Reporting authorized by OMB clearance number 21200056.)

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

(g) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, Georgia 30337.

This amendment becomes effective on January 17, 1985, to all persons except those to whom it has already been made effective immediately by telegraphic AD T84-24-53 issued December 9, 1984.

FOOTER: