AD 82-12-02 R1

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AD Number:
82-12-02 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BRITISH AEROSPACE (HAWKER SIDDELEY) Model HS/BH/DH 125 Airplanes
Subject:
Flap Structure
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
06/17/1985
Make:
Model:
BH.125 Series 400A | BH.125 Series 600A | DH.125 Series 1A | DH.125 Series 1A/R-522 | DH.125 Series ...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Superseded AD: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Superseded By: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: 82-12-02 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5058

AD NUMBER:   82-12-02 R1

SUBJECT HEADING:   Airworthiness Directives; BRITISH AEROSPACE (HAWKER SIDDELEY) Model HS/BH/DH 125 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective June 17, 1985.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   82-12-02 R1 BRITISH AEROSPACE (HAWKER SIDDELEY): Amendment 39-4392 as amended by Amendment 39-5058. Applies to British Aerospace Model HS/BH/DH 125 up to and including series 700 airplanes certificated in all categories except those airplanes incorporating Modification 252772. To prevent structural failure of the flap, accomplish the following within the next 100 hours time in service after the effective date of this AD or before the accumulation of 600 hours time in service on the airplane, whichever is later, unless already accomplished.

1. Visually inspect the flap outboard hinge nose ribs for cracks in accordance with the instructions in paragraph 2A of British Aerospace, Aircraft Group, 125 Service Bulletin (SB) No. 57-58, Revision 3, dated September 1, 1983.

a. If no cracks are found, no further action is necessary.

b. If cracks are found during the inspection required by paragraph 1, above, which do not exceed the criteria in paragraph 2A(5) of the service bulletin, reinspect at intervals not exceeding 40 hours time in service from the last inspection until a permanent repair is incorporated.

c. If cracks are found during the inspection required by paragraph 1 or during the repetitive inspection required by paragraph 1.b, above, which exceed the criteria in paragraph 2A(5) of the service bulletin, replace the flap with a serviceable flap or contact the manufacturer for instructions to make a permanent repair before further flight.

2. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD.

3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA Northwest Mountain Region.

The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1).

Amendment 39-4392 became effective June 8, 1982.

This amendment becomes effective June 17, 1985.

FOOTER: