AD 67-28-02

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AD Number:
67-28-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BRITISH AIRCRAFT Model BAC 1-11, 200 and 400 Series Airplanes
Subject:
Secondary Flap Transmission System
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/11/1970
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Superseded AD: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Superseded By: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: 67-28-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-911

AD NUMBER:   67-28-02

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

ACTION:  

SUMMARY:  

DATES:   Effective January 11, 1970.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
67-28-02 BRITISH AIRCRAFT: Amdt. 39-490 as amended by Amdt. 39-911. Applies to Model BAC 1-11, 200 and 400 Series airplanes.

Compliance required as indicated.

To prevent deterioration of the secondary flap transmission system due to corrosion in the magnesium bearing housings, accomplish the following:

(a) Within the next 250 hours' time in service after the effective date of this AD for airplanes with 2,750 or more hours' time in service, or for airplanes with less than 2,750 hours' time in service as of the effective date of this AD before the accumulation of 3,000 hours' time in service, and thereafter at intervals not to exceed 600 hours' time in service from the last inspection, visually inspect the support bearings in the flap secondary transmission shafting for signs of corrosion or stiffness in accordance with British Aircraft Corporation BAC 1-11 Alert Service Bulletin No. 27-A-PM 2757, Issue 1, or later ARB-approved issue, or an FAA-approved equivalent.

(b) If signs of corrosion or stiffness are found during the inspection required by paragraph (a), remove and dismantle the affected bearing assembly and inspect the interior of the bearing housing. If any corrosion is found, replace bearing housing before further flight with an unused magnesium bearing housing of the same part number or with an aluminum alloy bearing housing, in accordance with BAC 1-11 Service Bulletin No. 27-PM 2757 or later ARB-approved issue, or an FAA-approved equivalent.

(c) The repetitive inspections required by paragraph (a) may be made at intervals not to exceed 3,000 hours' time in service from the last inspection after the bearing assembly has been inspected in accordance with paragraph (b) and reassembled with the original magnesium bearing housing or an unused replacement magnesium bearing housing and the space between the bushings is coated with Jointing Compound J.C. 5A (VX3-100/200) or U.S. equivalent Hylomar SQ32(L) or SQ32(M).

(d) When a particular magnesium bearing housing is replaced with an aluminum alloy bearing housing in accordance with BAC 1-11 Service Bulletin 27-PM 2757 or later ARB- approved issue, or an FAA-approved equivalent, the repetitive inspection of that support bearing required by paragraph (a) may be discontinued.

(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Staff, FAA Europe, Africa, and Middle East Region may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the

Amendment 39-490 effective November 4, 196

This amendment (39-911) becomes effective January 11, 1970.

FOOTER: