AD 85-01-51

AD Final Rules - DRS_85-01-51.html
Copy URL
Print/Save as PDF
Document Versions
 Feedback
Details
AD Number:
85-01-51
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
EMBRAER Models EMB-110P1 and EMB-110P2 Airplanes
Subject:
Empennage Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
02/26/1985
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Superseded AD: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Superseded By: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: 85-01-51
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5004

AD NUMBER:   85-01-51

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

ACTION:  

SUMMARY:  

DATES:   Effective February 26, 1985.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
85-01-51 EMBRAER: Amendment 39-5004. Applies to Models EMB-110P1 and EMB-110P2 (all serial numbers) airplanes certificated in any category.

Compliance: Required within the next 18 hours time-in-service after the effective date of this AD unless either previously accomplished within the past 50 hours time-in-service or modified per paragraphs d) and e) of AD 83-14-09.

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

(1) Remove elevator preload springs from cross brace in empennage.

(2) Remove the cross brace in the empennage that contains the elevator preload springs (rivets will have to be drilled out).

(3) Gain access to the affected area through the inspection panel forward of bulkhead 33, releasing the elevator and rudder control cables if necessary for good access.

(4) Position a person in the empennage and inspect for loose, cocked or sheared rivets and signs of fretting in the areas indicated on Figure 2, Page 17 of EMBRAER Service Bulletin No. 110-53-019, Change 2, dated April 13, 1984, using mirror, light, and .010-inch feeler gauge. Attempt to insert feeler gauge between machined "U" channel and reinforcement ribs to determine if gap exists.

(5) The person stationed in the empennage should place his finger up against the machined "U" channel resting on reinforcement ribs left and right sides (P/N 4A-1419-07 L/H, P/N 4A-1419-08, P/N 4A-1419-05 L/H, and P/N 4A-1419-06) (see above service bulletin) while the horizontal stabilizer is deflected as indicated in (6) below.

(6) Position a person at a horizontal stabilizer tip and attempt to deflect the stabilizer tip "up and down approximately 3 inches, but no more than 3 inches. The person stationed inside the tail should try to detect any relative movement between structural members. Any movement requires removing all rivets attaching machined "U" channel and replacing them as specified in AD 83-14-09.

(7) Prior to further flight, correct any discrepancies found, reassemble and inspect assembly per AD 83-14-09.

(8) Report completion of inspection and any unsatisfactory conditions within 24 hours to the FAA, Airframe Branch, Atlanta Aircraft Certification Office; Telephone (404) 763-7407. Include in such reports the type and location of discrepancies, specifically identifying the discrepancy, location, material or component.

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

(10) An equivalent method of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, 1075 Inner Loop Road, College Park, Georgia 30337; Telephone (404) 763-7428.

This amendment becomes effective on February 26, 1985, to all persons except"those to whom it has already been made effective by telegram from the FAA dated January 10, 1985, and is identified as AD T85-01-51.

FOOTER: