AD 93-24-07

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AD Number:
93-24-07
Document Type:
AD Final Rules
Docket Number:
93-NM-185-AD
Subject Heading:
CORPORATE JETS LIMITED (FORMERLY BRITISH AEROSPACE, HAWKER SIDDELEY AVIATION, AND DE HAVILLAND AIRC...Show more
Subject:
Auxiliary Power Unit (APU) Fuel Control Enclosure Box
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
12/23/1993
Make:
Textron Aviation Inc.
Model:
BAe.125 Series 800A | BAe.125 Series 800A (C-29A) | BAe.125 Series 800A (U-125) | BH.125 Series 600A...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Superseded AD: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Superseded By: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: 93-24-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   93-NM-185-AD

AMENDMENT:   39-8756

AD NUMBER:   93-24-07

SUBJECT HEADING:   CORPORATE JETS LIMITED (FORMERLY BRITISH AEROSPACE, HAWKER SIDDELEY AVIATION, AND
DE HAVILLAND AIRCRAFT CO., LTD) Model BH/HS 125-600A, HS 125-700A, and BAe 125-800A Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective December 23, 1993.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
93-24-07 CORPORATE JETS LIMITED (FORMERLY BRITISH AEROSPACE, HAWKER SIDDELEY AVIATION, AND DE HAVILLAND AIRCRAFT CO., LTD): Amendment 39-8756. Docket 93-NM-185-AD.

Applicability: Model BH/HS 125-600A, HS 125-700A, and BAe 125-800A series airplanes equipped with a Sundstrand Turbomach auxiliary power unit (APU) Model T-62T-39 installed in accordance with Supplemental Type Certificate (STC) SA1923SW; certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent failure of the sealant installed around the over-temperature sensor located in the fuel control enclosure box of the APU, which could allow any fuel leakage from the APU into the fuel control enclosure box to leak into the aft equipment bay, thus creating a fire hazard, accomplish the following:

(a) Within 14 days after the effective date of this AD, deactivate the APU by pulling and collaring in the OFF position the circuit breakers for the APU ignition, APU fuel supply, and the electric power supply for the APU starter circuit.

(b) Within 14 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD in the AFM.

"Operation of the Sundstrand Turbomach auxiliary power unit Model T-62T-39 installed in accordance with Supplemental Type Certificate SA1923SW is prohibited."

(c) Replacement of the sealant installed around the over-temperature sensor located in the fuel control enclosure box of the APU with new sealant, in accordance with Arkansas Aerospace, Inc., Service Bulletin S.B. 49-72-02, Revision 1, dated August 13, 1993, constitutes terminating action for the requirements of paragraphs (a) and (b) of this AD. After such replacement, the APU may be reactivated and the AFM revision may be removed.

(d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Special Certification Office, FAA, Rotorcraft Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Special Certification Office.

NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Special Certification Office.

(e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.

(f) This amendment becomes effective on December 23, 1993.

FOOTER: