AD 90-17-05

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AD Number:
90-17-05
Document Type:
AD Final Rules
Docket Number:
90-NM-07-AD
Subject Heading:
Airworthiness Directives; BRANSON AIRCRAFT Beech Model 400, Mitsubishi Models MU-300-10 and MU-300 Airplanes
Subject:
Airplane Flight Manual (AFM) Changes - Fuel
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/17/1990
Make:
Textron Aviation Inc.
Model:
400 | MU-300 | MU-300-10
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Superseded AD: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Superseded By: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: 90-17-05
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-NM-07-AD

AMENDMENT:   39-6690

AD NUMBER:   90-17-05

SUBJECT HEADING:   Airworthiness Directives; BRANSON AIRCRAFT Beech Model 400, Mitsubishi Models MU-300-10 and MU-300 Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective September 17, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
90-17-05 BRANSON AIRCRAFT CORPORATION: Amendment 39-6690. Docket No. 90- NM-07-AD.

Applicability: Beech Model 400, Serial Numbers RJ-1 through RJ-50, and RJ-52 through RJ-65, which have been modified in accordance with Branson STC SA2744NM; Mitsubishi Model MU-300-10 airplanes, Serial Numbers A1001S.A. through A1011S.A., which have been modified in accordance with Branson STC SA2744NM; and Mitsubishi Model MU-300 airplanes, Serial Numbers A001S.A. through A091S.A., which have been modified in accordance with Branson STC SA1596NM; certificated in any category.

Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished.

To prevent the release of liquid and vaporous fuel into the cabin, and possible subsequent explosion and/or fire in the cabin, accomplish the following:

A. Accomplish either paragraph A.1. (Procedure 1) or paragraph A.2. (Procedure 2), below:

1. Procedure 1

a. Incorporate the following into the Operating Limitations Section of the FAA-approved Airplane Flight Manual (AFM):

FUSELAGE TANK REFUELING

Refueling of the fuselage tank is prohibited. Fuselage tank is deactivated.

NOTE: The above limitation supersedes any other AFM limitations which may be contradictory.

b. Defuel and drain the fuselage fuel tanks in accordance with the procedures of Chapter 12 of the appropriate Maintenance Manual. If JP-4 or Jet B fuel was the last fuel serviced, refuel and defuel twice with Jet A, Jet A-1 or JP-5 fuel. Use only the Fuselage Tank Fill system to refuel; do not gravity refuel the fuselage tanks.

c. Apply external power and energize the airplane's electrical distribution system.

d. Place the left (L) and right (R) Fuel Transfer (FUEL TRANS) switches, located on the overhead switch panel, to the "OFF" position. Verify that the "L and R FUEL TRANS OPEN" lights on the overhead switch panel are extinguished.

e. On the Forward (F) Circuit Breaker Panel, open and collar circuit breakers F135, "F TRANS PUMP"; F194, "RIGHT F FUEL TRANS"; and F195, "LEFT F FUEL TRANS"; using PACO plastic ring Part Number (PN) S-4933959-503, or equivalent.

f. Place the Fuselage Tank Fill System switch, located on the center console, to the "FILL" position. Verify that the fill system valve in-transit light on the center console does not illuminate momentarily and that the "L BOOST" light on the overhead switch panel does not illuminate. Return the Fuselage Tank Fill System switch to the "OFF" position.

g. Place the "L and R FUEL TRANS" switches, located on the overhead switch panel, to the "ON" position. Verify that the "L FUEL TRANS TRANSIT", "L FUEL TRANS OPEN", "R FUEL TRANS TRANSIT", and "R FUEL TRANS OPEN" lights do not illuminate. Return the "L and R FUEL TRANS" switches to the "OFF" position.

h. Remove power from the airplane's electrical distribution system and remove external power.

i. Fabricate a placard with letters at least .10 inch in height which states:

DO NOT FUEL FUSELAGE FUEL TANK.
FUSELAGE FUEL TANK IS DEACTIVATED.

Install this placard on the Fuselage Tank Fill System Switch panel, located on the center console, in full view of the pilot.

j. Fabricate a placard with letters at least .10 inch in height which states:

DO NOT USE TRANSFER. FUS TANK DEACTIVATED.


Install this placard on the overhead switch panel, in close proximity to the Fuel Transfer control switch panel.

k. Install Beech placard P/N 128-920210-1, or equivalent, centered on the fuselage fuel tank fuel filler access door.

2. Procedure 2

Upon completion of the requirements of Procedure 2, either gravity or transfer fueling of the fuselage fuel tank with all approved fuels is permitted.

a. Modify the fuel quantity probe mounting clamps and the transfer line clamps installation in the Branson extended range fuel tank and in the Beech/Mitsubishi aft fuselage fuel tanks, in accordance with the instructions in Branson Service Bulletin Number 2744-1, dated November 3, 1989 (for Beech Model 400 and Mitsubishi Model MU-300-10 airplanes), or in accordance with Branson Service Bulletin 1596-1, dated November 9, 1989 (for Mitsubishi Model MU-300 airplanes).

b. Install static charge dissipating charcoal-colored explosion suppression safety foam in the Branson extended range fuselage fuel tank in accordance with the instructions in Branson Service Bulletin Number 2744-2, dated November 3, 1989 (for Beech Model 400 and Mitsubishi Model MU-300-10 airplanes), or in accordance with Branson Service Bulletin 1596-2, dated November 9, 1989 (for Mitsubishi Model MU-300 airplanes).

c. Remove the existing blue-colored explosion suppression safety foam from the Beech/Mitsubishi aft fuselage fuel tank and install static charge dissipating charcoal-colored explosion suppression safety foam in accordance with the instructions in Part II of Beechcraft Mandatory Service Bulletin Number 2338, dated November 1989 (for Beech Model 400 and Mitsubishi Model MU-300-10 airplanes), or in accordance with Part II of Mitsubishi Heavy Industries Service Bulletin 28-001, dated November 21, 1989 (for Mitsubishi Model MU-300 airplanes).

d. If Procedure 2 is accomplished after accomplishing Procedure 1 (described in paragraph A.1., above), perform the following:

1. Remove the AFM limitation imposed by Procedure 1, subparagraph A.1.a., above.

2. Remove the circuit breaker collars and reset circuit breakers F135, F194, and F195, which were opened and collared by Procedure 1, subparagraph A.1.e., above.

3. Remove the placard from the Fuselage Tank Fill System Switch panel, which was installed by Procedure 1, subparagraph A.1.i., above.

4. Remove the placard from the overhead switch panel, which was installed by Procedure 1, subparagraph A.1.j., above.

5. Remove Beech P/N 128-920210-1 placard, or its equivalent, from the fuselage fuel tank fuel filler access door, which was installed by Procedure 1, subparagraph A.1.k., above.

B. An alternate means of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be approved by the Manager, Wichita Aircraft Certification Office, FAA, Central Region.

NOTE: The request should be submitted to the Manager, Wichita Aircraft Certification Office, ACE-140W, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Wichita Aircraft Certification Office.

C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.

All persons affected by this directive who have not already received the appropriate service information from the manufacturers may obtain copies upon request to Branson Aircraft Corporation, 3790 Wheeling Street, Denver, Colorado 80239 and Beech Aircraft Corporation (United States agents for Mitsubishi Heavy Industries, Incorporated), P. O. Box 85, Wichita, Kansas 67201-0085. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue, S.W., Renton, Washington, or at the FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas.

Airworthiness Directive 90-17-05 supersedes AD 89-26-11, Amendment 39-6426.

This amendment (39-6690, AD 90-17-05) becomes effective on September 17, 1990.

FOOTER: