AD 88-05-02

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AD Number:
88-05-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BRITISH AEROSPACE (BAe) PLC Model DH/BH/HS 125 Series Airplanes
Subject:
Airplane Structure
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/06/1988
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Superseded AD: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Superseded By: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: 88-05-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-5858

AD NUMBER:   88-05-02

SUBJECT HEADING:   Airworthiness Directives; BRITISH AEROSPACE (BAe) PLC Model DH/BH/HS 125 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 6, 1988.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   88-05-02 BRITISH AEROSPACE (BAe) PLC: Amendment 39-5858. Applies to Model DH/BH/HS 125 series airplanes listed in BAe 125 Service Bulletins 57-67 and 53-63, both dated February 27, 1987, certificated in any category.

Compliance is required as indicated, unless previously accomplished.

To detect fatigue cracking in the airplane structure, which could result in the inability of the structure to meet required loads, accomplish the following:

A. For airplane serial numbers as listed in BAe-125 Service Bulletin 57-67 dated February 27, 1987: Prior to the accumulation of 12,000 flights, or within 8 months after the effective date of this AD, whichever occurs later, visually inspect the wing bottom skin for cracks at the flap outboard hinge fitting in accordance with that service bulletin. Repair detected cracks prior to further flight in accordance with an FAA approved method.

B. For airplane serial numbers as listed in BAe-125 Service Bulletin 53-63, dated February 27, 1987: Prior to the accumulation of 7,500 flights, or within 6 months after the effective date of this AD, whichever occurs later, visually inspect the fuselage skin beneath the canopy blister for cracks in accordance with that service bulletin. Repair detected cracks prior to further flight in accordance with an FAA approved method.

C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region.

D. 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 required by this AD.

All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Inc., Service Bulletin Librarian, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.

This amendment becomes effective April 6, 1988.

FOOTER: