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90-07-08 R1: 90-07-08 R1 S.E.L.A. LABORATOIRE ABADIE (SELA): Amendment 39-6546 as revised by Amendment 39-6627.
Applicability: Fluorescent lighting lamp connectors, Part Number (P/N) 3185-1A, and Remote Power Units (RPU), P/Ns TR 992, TR 992A, TR 992-1, TR 992-3, TR 992-4, and TR 992-5, manufactured by SELA, and installed in, but not limited to AMD-BA Falcon Models 10, 20, 50, 900, BAe Jetstream Models 3101 and 3201, CASA Model 235, Embraer Model EMB-120, and SAAB-Scania Model SF 340A airplanes certificated in any category.
NOTE 1: SELA and Aerospace Lighting Corporation (ALC) components are similar in size, shape and color and have similar part numbers. They may be identified by trademark. The SELA RPU can be identified by a starburst pattern incorporating the text "laboratoire, abadie, France." The ALC RPU can be identified by a stylized ALC logo with "Aerospace Lighting Corp" in smaller print beneath the logo. The ALC lamp connector has "ALC" molded into the gray body of theconical piece of the connector body with a black lock ring. The SELA lamp connector is stamped in yellow ink on a black connector body with a gray lock ring. The ALC lamp can be positively identified by the presence of a small hole in the locking channel of each blue plastic end piece.
Compliance: Required as indicated in the body of the AD, unless already accomplished per AD 90-07-08.
To prevent smoke, fire, and possible electrical shock, or electromagnetic interference to flight critical or essential systems, accomplish the following:
(a) If the cabin fluorescent lighting system is not deactivated, within the next 30 days after the effective date of this AD, and thereafter until the actions described in paragraph (b) of this AD are accomplished, insert a copy of this AD into the limitations section of the airplane flight manual, and prior to each takeoff where cabin fluorescent lights are used: Visually check the cabin fluorescent lighting, and remedy as follows:(1) Replace all failed lamps prior to further flight.
(2) Replace all failing lamps which have noticeably less illumination (darker) than adjacent lamps within the next 10 hours time-in-service after the lamp condition is found.
(b) If the cabin fluorescent lighting system is not deactivated, within the next 120 days after the effective date of this AD, visually inspect all cabin fluorescent lighting system components, and prior to further flight remedy all defects found following the instructions in this AD.
If the cabin fluorescent lighting system is deactivated as described in paragraph (c) of this AD, the inspection described in this paragraph is not required until the fluorescent lighting system is reactivated.
NOTE 2: The aircraft manufacturer's maintenance manual, the installer's maintenance manual, other service information, SELA Technical Data Sheet (TDS) REF 90/11980, dated February 9, 1990, or Bigorre Aerospace Corporation (BAC) "How To" Number 1Manual, dated May 10, 1989, contains information which supplements the instructions described in this AD. This information is important to proper maintenance and replacement of defective components.
(1) Insure that the aircraft manufacturer's instructions regarding electrical safety precautions are followed.
NOTE 3: Hazardous voltages may exist in the fluorescent lighting system.
(2) Visually inspect all installed SELA RPUs (P/Ns) TR992, TR 992A, TR 992-1, TR 992-3, TR 992-4, and TR 992-5 wiring harnesses:
(i) If charred, burned, or peeling insulation on wires is found, replace the RPU assembly as a unit. No repairs of the high voltage wires may be made except for the installation of the lamp connector.
(ii) Remove and discard any foil insulation installed around the RPU.
(iii) Remove all tywraps where wires may be bundled together and inspect the wire insulation for crimps, kinks, or abrasion. Replace the RPU if the insulation is damaged. Donot fold the wire harness against itself.
(iv) Insure that the wire insulation is protected from abrasion against the aircraft structure by use of grommets, standoffs, or similar items.
(v) Measure the length of the output wires from the RPU termination to the lamp connectors. Insure that each high voltage wire does not exceed 78 inches (2M) in length. If the wire exceeds 78 inches, cut the lamp connector end of the wire and install a new fitting (P/N 3185-5) by stripping between 0.12 inch (3mm), and 0.20 inch (5mm) of the insulation from the end of the wire and crimping the fitting onto the wire with Deutsch crimping pliers P/N 15500 and SELA positioner P/N 3185-8 in place of Deutsch positioner 20 MS (red), or Burndy M10S-1 crimping tool with S-6A die, or SELA/BAC approved equivalent. Do not solder the wire into the fitting.
(3) Each lamp shall be installed only into 2 connectors made by the same manufacturer as the
lamp.
(4) Visually inspect all lamp connector assemblies and for each such assembly:
(i) Replace all burned, melted, cracked, or incorrectly installed lamp connectors, (SELA TDS REF 90/11980 dated February 9, 1990, provides installation criteria).
(ii) Insure that the lamp connector spring (P/N 3185-22), is free to move within the connector, is unbroken and undamaged, and the wire does not bind within the connector. After the lamp connector is correctly installed on the lamp, the spring will not move freely.
(iii) Insure that the contact fitting (P/N 3185-5) is properly crimped and is not soldered onto the wire.
(iv) Insure that the contact fitting is installed flush over the end of the lamp contact with no gap between the fitting and the mating end of the lamp.
(v) Insure that the lamp connector body (P/N 3185-7) is installed first over the lamp until it "clicks" into position. There should be no more than a 0.04 inch (1mm) gap between the connector body and the lamp end. Slide thelocking sleeve (P/N 3185-15) over the connector body. Do not slide the locking sleeve onto the connector before installation on the lamp.
(vi) Insure that there are no bare wires or stray wire strands at the end of the connector after assembly.
NOTE 4: High voltage potentials may exist between adjacent output wires and hasten the formation of arcing damage.
(5) Insert the lamp into no more than 2 clips insuring a snug fit. Insure that lamp clips are properly secured to the airplane structure. Reposition any lamps that contact this structure.
(c) The cabin fluorescent lighting system may be deactivated in accordance with the following instructions:
(1) If the deactivation is accomplished by tripping a circuit breaker (CB), then the CB must be tywrapped in the tripped position, or a collar installed which prevents resetting of the CB.
NOTE 5: Some airplane installations may power this system through more than one switch or circuit. In those cases,the fluorescent lighting system power lead must be removed, capped, and stowed so that no combination of switch selections will power the cabin fluorescent lights.
(2) A placard is placed in proximity to the cabin fluorescent lighting system control stating that the system is deactivated.
(3) That prior to each boarding of passengers at night or during reduced light conditions, the flight crew must ensure that one passenger reading light per row and all vestibule lights are illuminated.
(4) That prior to deplaning passengers at night or during reduced light conditions, the flight crew:
(a) Request that all passengers turn on the reading light above their seat, and
(b) Ensure that the vestibule lighting is illuminated.
(5) All other cabin lights are required to be operable.
(d) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.
(e) The visual check, only, required by paragraph (a) of this AD, may be accomplished by a certificated flightcrew member.
NOTE 6: When the checks required by paragraph (a) of this AD are accomplished by a flightcrew member pursuant to the restrictions specified in paragraph (e) of this AD, maintenance records must be maintained as required by FAR 91.173, 121.380, or 135.439 as applicable and a maintenance record is not required unless a defect is found.
(f) An alternate method of compliance or adjustment of the compliance times which provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium.
NOTE 7: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff.
All persons affected by this directive may obtain copies of the documents referred to herein upon request to S.E.L.A. Laboratoire Abadie, BP No. 1 65500, Vic En Bigorre, France; Telephone (33) 62.96.71.56; Facsimile (33) 62.96.23.09, or Bigorre Aerospace Corporation (BAC), Suite 1107, 6543-46th Street North, Pinellas Park, Florida 34665; Telephone (813) 525-8115; Facsimile (813) 522-5820; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
This amendment revises AD 90-07-08, Amendment 39-6546.
This amendment (39-6627, AD 90-07-08 R1) becomes effective on July 2, 1990.
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