AD 77-15-02

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AD Number:
77-15-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; HAWKER SIDDELEY AVIATION, LIMITED Model HS-748 2A Airplanes
Subject:
Aileron Control
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/15/1977
Make:
BAE Systems (Operations) Limited
Model:
HS 748 Series 2A
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Superseded AD: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Superseded By: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: 77-15-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-2972

AD NUMBER:   77-15-02

SUBJECT HEADING:   Airworthiness Directives; HAWKER SIDDELEY AVIATION, LIMITED Model HS-748 2A Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective August 15, 1977.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
77-15-02 HAWKER SIDDELEY AVIATION, LIMITED: Amendment 39-2972. Applies to Model HS-748, Series 2A airplanes, certificated in all categories.

Compliance is required as indicated.

To prevent a possible loss of aileron control, accomplish the following:

(a) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 100 hours time in service from the last inspection, visually inspect the aileron hinge structures of the right and left wings in the areas of the outer and center hinges for damage, in accordance with the instructions set forth in Part 2A of the section entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/25, dated October 15, 1973, or an FAA-approved equivalent.

(b) If, as a result of an inspection required by paragraph (a) of this AD, damage, in the form of cracks, loose rivets, or corroded support bearings or pivot bolts is found in any of the areas specified in paragraph (a) of this AD, before further flight, perform an internal inspection of the aileron hinge ribs where they attach to the rear spar of the wing in accordance with the instructions set forth in Part 2B of the section entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/25, dated October 15, 1973, or an FAA- approved equivalent.

(c) If, as a result of an inspection required by either paragraph (a) or (b) of this AD, damage, in the form of cracks, loose rivets, or corroded support bearings or pivot bolts is found, before further flight, replace or repair the damaged, loose, or corroded parts in accordance with Part 2C of the section entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/25, dated October 15, 1973, or an FAA-approved equivalent, and continue to inspect in the areas specified and at the intervals established in paragraphs (a) and (b) of this AD, as required.

(d) Within the next 1000 hours time in service after the effective date of this AD, unless already accomplished, install strengthened gusset plates to reinforce the outer and center aileron hinge ribs at both the right and left wings, in accordance with Modification 4873 as described in Part 2, entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/28, dated January 2, 1974, or an FAA-approved equivalent.

(e) Within the next 1000 hours time in service after the effective date of this AD, unless already accomplished, install reinforcing straps at the top and bottom surfaces of the aileron spar area of both the right and left wings at the outboard aileron hinge positions, in accordance with Modification 4874 as described in Part 2, entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/27, dated January 2, 1974, or an FAA-approved equivalent.

(f) Within the next 1000 hours time in service after the effective date of this AD, unless already accomplished, install the reinforcing plates on the right and left wing tips on the rear diaphragm in accordance with Modification 4875 as described in Part 2, entitled "Accomplishment Instructions" of Hawker Siddeley Service Bulletin No. 57/26, dated January 2, 1974, or an FAA-approved equivalent.

(g) Upon accomplishment of the modifications specified in paragraphs (d), (e), and (f) of this AD, the inspections required by paragraphs (a) and (b) of this AD, may be terminated.

This amendment becomes effective August 15, 1977.

FOOTER: