AD 83-15-08 R1

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AD Number:
83-15-08 R1
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BRITISH AEROSPACE Model BAC 1-11 200 and 400 Series Airplanes
Subject:
Fuselage Skin Lap Joints
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/07/1989
Make:
Airbus SAS
Model:
BAC 1-11 200 Series | BAC 1-11 400 Series
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Superseded AD: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Superseded By: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: 83-15-08 R1
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-6255

AD NUMBER:   83-15-08 R1

SUBJECT HEADING:   Airworthiness Directives; BRITISH AEROSPACE Model BAC 1-11 200 and 400 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective on August 7, 1989.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   83-15-08 R1 BRITISH AEROSPACE: Amendment 39-4697 as revised by Amendment 39- 6255.

Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category.

Compliance: Required as indicated unless previously accomplished.

To prevent structural failure of the fuselage, accomplish the following:

A. Perform initial and repetitive visual and eddy current inspections of fuselage skin lap joints for cracks and loose rivets at the intervals shown in Table I of this AD, in accordance with Section 2, of the Accomplishment Instructions, of British Aerospace Alert Service Bulletin 53-A-PM5726, Issue 3, dated May 26, 1988.

B. Repair any identified cracks or loose rivets prior to further flight, in accordance with paragraph 2.4.2 of British Aerospace Alert Service Bulletin 53-A-PM5726, Issue 3, dated May 26, 1988; or Chapter 53-02-0, Figure 89, of the BAC 1-11 Structural Repair Manual, whichever is appropriate; or in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region.

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

NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113.

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 the requirements of 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, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington.

This AD revises AD 83-15-08, Amendment 39-4697.

This amendment (39-6255, AD 83-15-08 R1) becomes effective on August 7, 1989.

TABLE I


Airplanes
Affected	AD 83-15-08
Previously
Complied
With?	Initial Inspection
Threshold for this AD	Repetitive Inspection
Interval
Airplanes
operated only
at standard
cabin pressure
of 7.5 psi
max cabin
differential
pressure	NO	Whichever occurs later:

-Within 1,250 landings
after September 6,1983
(effective date of AD
83-15-08); or	For airplanes with
less than 50,000
landings:

Visual Inspection:
-Every 1,250 landings
		-Upon accumulating the
number of landings
determined by Figure 1
of British Aerospace
Alert Service Bulletin
53-A-PM5726, Revision 3,
dated May 26, 1988	Eddy Current Inspection:
-Every 3,750 landings





For airplanes with
50,000 or more
landings:
	YES	Visual Inspection:
-Within 1,250 landings
after the last visual
inspection in accordance
with AD 83-15-08

Eddy Current Inspection:
-Within 3,750 landings
after the last eddy
current inspection in
accordance with
AD 83-15-08	Visual Inspection:
-Every 1,875 landings

Eddy Current Inspection:
-Every 3,750 landings
Airplanes
operated at
increased
cabin pressure
of 7.75 psi
max cabin
differential
pressure	NO	Whichever occurs later:

-Within 1,250 landings
after September 6,1983
(effective date of AD
83-15-08); or

-Upon accumulation of
35,000 landings.	Visual Inspection:
-Every 1,600 landings

Eddy Current Inspection:
-Every 3,200 landings
	YES	Visual Inspection:
-Within 1,600 landings
after the last visual
inspection in accordance
with AD 83-15-08

Eddy Current Inspection:
-Within 3,200 landings
after the last eddy
current inspection in
accordance with AD
83-15-08	
Airplanes
operated at
increased
cabin pressure
of 8.2 psi max
cabin
differential
pressure	NO	Whichever occurs later:

-Within 1,250 landings
after September 6,
1983 (effective date of
AD 83-15-08); or

-Upon accumulation of
30,000 landings.	Visual Inspection:
-Every 1,250 landings

Eddy Current Inspection:
-Every 2,500 landings
	YES	Visual Inspection:
-Within 1,250 landings
after the last visual
inspection in accordance
with AD 83-15-08.

Eddy Current Inspection:
-Within 2,500 landings
after the last eddy
current inspection in
accordance with AD
83-15-08.	
Airplanes for
which cabin
max operating
pressure is
reduced to
6.0 PSI max
cabin
differential
pressure	NO
or
YES
(as
applicable)	Visual Inspection:
-The same as shown above
for the max cabin
differential pressure
applicable to the
airplane in question.
Eddy Current Inspection:
-Every 5,600 landings
Eddy Current Inspection:

-The same as shown above
for the max cabin
differential pressure
applicable to the
airplane in question.	For all airplanes:



Visual Inspection:
-Every 1,875 landings


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