AD 77-13-10

AD Final Rules - DRS_77-13-10.html
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AD Number:
77-13-10
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; HAWKER SIDDELEY AVIATION, LTD Model DH/BH-125 Airplanes Series
Subject:
Aileron Inner Hinge Bracket
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/25/1977
Make:
Textron Aviation Inc.
Model:
BH.125 Series 400A | BH.125 Series 600A | DH.125 Series 1A | DH.125 Series 1A-522 | DH.125 Series 1A...Show more
Product Type:
Aircraft
Product Subtype:
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Superseded AD: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Superseded By: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: 77-13-10
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2935

AD NUMBER:   77-13-10

SUBJECT HEADING:   Airworthiness Directives; HAWKER SIDDELEY AVIATION, LTD Model DH/BH-125 Airplanes Series

ACTION:  

SUMMARY:  

DATES:   Effective July 25, 1977.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
77-13-10 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2935. Applies to Hawker Siddeley Aviation, Ltd., Model DH/BH-125 airplanes, all series, with manufacturer's serial numbers 256056 and below and serial number 256061, certificated in all categories.

Compliance is required as indicated, unless already accomplished.

To detect excessive boss thickness that may exist on certain aileron inner hinge brackets (R/H and L/H) which can result in insufficient engagement and prevent self locking of the cable guard in the thread insert, accomplish the following:

(a) Within 100 hours time in service after the effective date of this AD, measure the thickness of the boss of the upper and lower flange of the aileron inner hinge bracket at the point where the cable guard, P/N 25CW593-1 or -3, is mounted, in accordance with paragraphs (A)(1) and (2) of the Section titled "Accomplishment Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin SB 57-51, dated April 20, 1976, or an FAA-approved equivalent.

(b) If the boss thickness at the cable guard mounting, measured in accordance with paragraph (a) of this AD, is found to be more than .35 inches at the top flange or more than .31 inches at the bottom flange, inspect the cable guards before further flight for proper security and accomplish the following:

(1) Replace cable guards found improperly secured, loose, or missing, before further flight, with new cable guards fabricated and installed in accordance with paragraph (A)(3)(b) of the Section entitled "Accomplished Instructions" of Hawker Siddeley Aviation, Ltd., Service Bulletin SB 57-51, dated April 20, 1976, or an FAA-approved equivalent. New cable guards fabricated and installed in accordance with this paragraph must have an exposed thread length tolerance in the range of .31 to .32 inches to provide sufficient engagement of the thread insert locking device mounted in the boss.

(2) Cable guards found to be secure must be replaced with the new cable guard in accordance with paragraph (b)(1) of this paragraph within 300 hours time in service after the inspection required by this paragraph.

(c) Prior to the installation of an aileron inner bracket assembly, or a cable guard that is part of an assembly held as a spare, measure the boss thickness in accordance with paragraph (a) of this AD and if the dimensions exceed the limits specified in the lead-in sentence of paragraph (b) of this AD, replace the cable guards with new cable guards in accordance with paragraph (b)(1) of this AD.

This amendment becomes effective July 25, 1977.

FOOTER: