AD 78-05-09

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AD Number:
78-05-09
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; BRITISH AIRCRAFT CORPORATION Model BAC 1-11 Series Airplanes
Subject:
Fuel Boost Pump Electric Connectors
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/23/1978
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Superseded AD: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Superseded By: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: 78-05-09
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-3154

AD NUMBER:   78-05-09

SUBJECT HEADING:   Airworthiness Directives; BRITISH AIRCRAFT CORPORATION Model BAC 1-11 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective March 23, 1978.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
78-05-09 BRITISH AIRCRAFT CORPORATION: Amendment 39-3154. Applies to BAC 1- 11, Model/Types 203/AE, 204/AF, 212/AR, 215/AU, 201/Z/AC, 401/AK, 410/AQ, 419/EP, and 412A/EB airplanes.

Compliance is required as indicated.

To prevent destruction of the fuel boost pump electrical connector accomplish the following:

(a) Within the next 300 hours airplane time in service after the effective date of this AD, unless already accomplished, comply with the following:

(1) Permanently install a placard at all cockpit fuel boost pump circuit breakers, using white letters on a red background, to read as follows:


DO NOT RESET IN FLIGHT

(2) Insert in the limitations section of the Airplane Flight Manual the statement: "Do not reset fuel boost pump circuit breakers until the affected boost pump electrical connector has been inspected in accordance with paragraph 2.3.7 of BAC Alert Service Bulletin 28-A-PM 5220, Issue 4, dated October 22, 1975, or an FAA-approved equivalent."

(3) On airplanes equipped with a center fuel tank, permanently, install a placard in the cockpit next to the center fuel tank transfer pumps, using white letters on a red background, to read as follows:

TURN TRANSFER PUMP OFF WHEN L.P. LIGHT ILLUMINATES

(4) For airplanes equipped with a center fuel tank, insert in the limitations section of the Airplane Flight Manual the statement: "Turn center tank fuel transfer pumps "off" when the L.P. light illuminates".

(b) For airplanes equipped with fuel boost pump and housing TRW P/N 249000-6 or Plessey P/N 570-8-21225 (which includes boost pump housing connector assembly TRW P/N 209237-1 or Plessey P/N 570-1-21227), comply with the following:

(1) Prior to accumulation of 6,000 hours total time in service on the fuel boost pump housing connector assembly, or within the next 100 hours airplane time in service after the effective date of this AD, whichever occurs later, unless already accomplished within the preceding 100 hours airplane time in service, and thereafter at intervals not to exceed 200 hours airplane time in service from the last inspection, until compliance with paragraph (g) of this AD, comply with paragraphs (d), (e) and (f) of this AD.

(2) Prior to the accumulation of 6,000 hours total time in service on the fuel boost pump housing connector assembly, or within the next 1,500 hours airplane time in service after the effective date of this AD, whichever occurs later, unless already accomplished within the preceding 1,500 hours airplane time in service, and thereafter at intervals not to exceed 6,000 hours airplane time in service from the previous compliance, comply with paragraph (g) of this AD.

(c) For airplanes equipped with fuel boost pump and housing, TRW P/N 249000-7 or Plessey P/N 570-8-23456 (which includes boost pump housing connector assembly TRW P/N 209237-1 or Plessey P/N 570-1-21227), comply with the following:

(1) Prior to accumulation of 10,000 hours total time in service on the fuel boost pump housing connector assembly, or within the next 100 hours airplane time in service after the effective date of this AD, whichever occurs later, unless already accomplished within the preceding 100 hours airplane time in service, and thereafter at intervals not to exceed 200 hours airplane time in service from the last inspection, until compliance with paragraph (g) of this AD, comply with paragraphs (d), (e), and (f) of this AD.

(2) Prior to the accumulation of 10,000 hours total time in service on the fuel boost pump housing connector assembly, or within the next 1,500 hours airplane time in service after the effective date of this AD, whichever occurs later, unless already accomplished within the preceding 1,500 hours airplane time in service, and thereafter at intervals not to exceed 10,000 hours airplane time in service from the previous compliance, comply with paragraph (g) of this AD.

(d) Visually inspect all fuel boost pumps on the airplane by operating them for 10 minutes and inspecting for signs of fuel leakage at the fuel pump conduit drains in accordance with paragraph 2.3.3 of BAC Alert Service Bulletin 28-A-PM 5220, Issue 4, dated October 22, 1975, (hereinafter referred to as BAC ASB), or an FAA-approved equivalent.

(e) If, during any inspection required by this AD, fuel leakage is detected, identify the pump causing the leak and visually inspect its housing connector assembly, TRW P/N 209237-1 or Plessey P/N 570-1-21227, within the boost pump housing, and its associated fuel boost pump electrical connector for evidence of arcing, overheating, or deterioration of the 'O' ring in accordance with paragraph 2.3.7 of BAC ASB, or an FAA-approved equivalent.

(f) Where evidence of arcing, overheating, or deterioration of the 'O' ring seal is found in either the boost pump housing or the electrical connector as a result of an inspection required by this AD, replace the affected parts with serviceable parts before further flight, except that the airplane may be flown in accordance with FAR Sections 21.197 and 21.199 to a base where the work can be performed, provided that the affected pumps are isolated by pulling and clipping the affected pump circuit breaker and placarding the affected pump ON-OFF switch in the cockpit third crewman's panel with the word, INOPERATIVE.

(g) Disassemble the electrical connector assembly, perform the inspections, and replace the appropriate parts in accordance with paragraphs 2.3.10, 2.3.11, except for the replacement of "thin" nuts with "full" nuts, and 2.3.12 of BAC ASB, or an FAA-approved equivalent.

(h) Upon the request of an operator, the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York 09667, may approve alternate repetitive inspection intervals and inspection procedures to facilitate continued operations by the operator, if data substantiating such action are submitted by the operator.

This amendment becomes effective March 23, 1978.

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