Airworthiness Directive · Amendment 39-13797 · Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 Series Airplanes
Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and EMB-145 Series Airplanes
Model EMB-135 and EMB-145 series airplanes; as identified in EMBRAER Alert Service Bulletin 145-36-A018, Change 01, dated October 20, 2000; certificated in any category.
This amendment supersedes an existing airworthiness directive (AD), applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes, that currently requires revising the airplane flight manual and eventual disconnection of the precooler differential pressure switches. This amendment expands the applicability of the existing AD. This amendment also requires a one-time inspection of those additional airplanes to ensure the disconnection and insulation of the electrical connectors of certain precooler differential pressure switches located in the left and right pylons; and disconnection and insulation of the connectors, if necessary. The actions specified by this AD are intended to prevent incorrect operation of the precooler differential pressure switches, which could result in inappropriate automatic shutoff of the engine bleed valve, and consequent inability to restart a failed engine using cross-bleed from the other engine or possible failure of the anti-ice system. This action is also necessary to ensure that the flightcrew is advised of the procedures necessary to restart an engine in flight using the auxiliary power unit. This action is intended to address the identified unsafe condition.
To prevent incorrect operation of the precooler differential pressure switches, which could result in inappropriate automatic shutoff of the engine bleed valve, and consequent inability to perform engine cross-bleed restarts or possible failure of the anti-ice system; and to ensure that the flightcrew is advised of proper procedures to restart an engine in flight using the auxiliary power unit; accomplish the following:
(a) For airplanes identified in AD 2000-13-02, amendment 39-11801: Within 24 hours after July 3, 2000 (the effective date of AD 2000-13-02, amendment 39-11801), revise the Limitations Section of the AFM to include the following statements (this may be accomplished by inserting a copy of this AD into the AFM; following accomplishment of paragraph (c) of this AD, the revisions required by this paragraph may be removed from the AFM):
(b) For airplanes identified in AD 2000-13-02, amendment 39-11801: Within 24 hours after July 3, 2000, replace the existing “ENGINE AIRSTART” procedure in the Abnormal Procedures Section of the AFM with the following procedures (this may be accomplished by inserting a copy of this AD into the AFM):
Affected engine:
One Electric Fuel Pump (A or B)—ON
Ignition—AUTO
Start/Stop Selector—STOP
Engine Bleed—CLOSE
Thrust Lever—IDLE
Airspeed and Altitude—REFER TO AIRSTART ENVELOPE
Perform an assisted start or windmilling, as required.
CAUTION: IN ICING CONDITIONS USE CROSSBLEED START ONLY, TO AVOID LOSS OF ANTI-ICE SYSTEM PERFORMANCE.
Crossbleed Start:
N2 (operating engine)—ABOVE 80%
Crossbleed—AUTO OR OPEN
Engine Bleed (operating engine)—OPEN
Start/Stop Selector—START, THEN RUN
Engine Indication—MONITOR
Check ITT and N2 rising. Observe limits. Check ignition and fuel flow indication at 10% N2.
APU bleed start:
APU—START
APU Bleed—OPEN
Crossbleed—AUTO
Engine Bleed (operating engine)—CLOSE
Start/Stop Selector—START, THEN RUN
Engine Indication—MONITOR
Check ITT and N2 rising. Observe limits. Check ignition and fuel flow indication at 10% N2.
Airspeed—ABOVE 260 KIAS
Minimum N2—12%
Start/Stop Selector—START, THEN RUN
ITT and N2—MONITOR
NOTE:
Windmilling start will be slower than an assisted start.
Windmilling start with N2 above 30% and increasing, the loss of altitude may be minimized, by reducing airspeed.
Start will be faster if ITT is below 320 °C.
Affected Engine Bleed—AS REQUIRED
Crossbleed—AUTO
APU Bleed—AS REQUIRED”
(c) For airplanes identified in AD 2000-13-02, amendment 39-11801: Within 100 flight hours after July 3, 2000, disconnect the electrical connector from the precooler differential pressure switches in the left and right engine pylons, in accordance with EMBRAER Alert Service Bulletin 145-36-A018, dated April 14, 2000; or Change 01, dated October 20, 2000. Following accomplishment of this paragraph, the AFM revision required by paragraph (a) of this AD may be removed from the AFM.
(d) For airplanes having serial numbers 145245, 145250 through 145255 inclusive, 145258 through 145262 inclusive, 145264 through 145324 inclusive, 145326, and 145327: Within 14 days after the effective date of this AD, revise the Limitations Section of the AFM to include statements approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA (Revision 56 to the EMBRAER EMB-145 AFM is one approved source of statements); or the following statements (this may be accomplished by inserting a copy of this AD into the AFM; following accomplishment of paragraph (f) of this AD, the revisions required by this paragraph may be removed from the AFM):
(e) For airplanes having serial numbers 145245, 145250 through 145255 inclusive, 145258 through 145262 inclusive, 145264 through 145324 inclusive, 145326, and 145327: Within 14 days after the effective date of this AD, replace the existing “ENGINE AIRSTART” procedure in the Abnormal Procedures Section of the AFM with statements approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate (Revision 56 to the EMBRAER EMB-145 AFM is one approved source of statements); or the following procedures (this may be accomplished by inserting a copy of this AD into the AFM):
Affected engine:
One Electric Fuel Pump (A or B)—ON
Ignition—AUTO
Start/Stop Selector—STOP
Engine Bleed—CLOSE
Thrust Lever—IDLE
Airspeed and Altitude—REFER TO AIRSTART ENVELOPE
Perform an assisted start or windmilling, as required.
CAUTION: IN ICING CONDITIONS USE CROSSBLEED START ONLY, TO AVOID LOSS OF ANTI-ICE SYSTEM PERFORMANCE.
Crossbleed Start:
N2 (operating engine)—ABOVE 80%
Crossbleed——AUTO OR OPEN
Engine Bleed (operating engine)—OPEN
Start/Stop Selector—START, THEN RUN
Engine Indication—MONITOR
Check ITT and N2 rising. Observe limits. Check ignition and fuel flow indication at 10% N2.
APU bleed start:
APU—START
APU Bleed—OPEN
Crossbleed—AUTO
Engine Bleed (operating engine)—CLOSE
Start/Stop Selector—START, THEN RUN
Engine Indication—MONITOR
Check ITT and N2 rising. Observe limits. Check ignition and fuel flow indication at 10% N2.
Airspeed—ABOVE 260 KIAS
Minimum N2—12%
Start/Stop Selector—START, THEN RUN
ITT and N2—MONITOR
NOTE:
Windmilling start will be slower than an assisted start.
Windmilling start with N2 above 30% and increasing, the loss of altitude may be minimized, by reducing airspeed.
Start will be faster if ITT is below 320 °C.
Affected Engine Bleed—AS REQUIRED
Crossbleed—AUTO
APU Bleed—AS REQUIRED”
(f) For airplanes having serial numbers 145245, 145250 through 145255 inclusive, 145258 through 145262 inclusive, 145264 through 145324 inclusive, 145326, and 145327: Within 100 flight hours after the effective date of this AD, perform a one-time general visual inspection to ensure that electrical connector P1904 located in the right pylon is insulated and disconnected from precooler differential pressure switch S0354, and to ensure that electrical connector P1904 or P2252 located in the left pylon is insulated and disconnected from precooler differential pressure switch S0355, per the Accomplishment Instructions of EMBRAER Alert Service Bulletin 145-36-A018, Change 01, dated October 20, 2000. Following accomplishment of paragraph (f)(1), (f)(2), or (f)(3) of this AD, as applicable, the AFM revision required by paragraph (d) of this AD may be removed from the AFM.
(1) If all connectors are disconnected and insulated, no further action is required by this paragraph.
(2) If any connector is connected to a precooler differential pressure switch, prior to further flight, disconnect and insulate the connector per the Accomplishment Instructions of the alert service bulletin.
(3) If any connector is disconnected from a precooler differential pressure switch, but is not insulated, prior to further flight, insulate the connector per the Accomplishment Instruction of the alert service bulletin.
Note 1: For the purposes of this AD, a general visual inspection is defined as: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.”
(g) Actions accomplished before the effective date of this AD, per the Accomplishment Instructions of EMBRAER Alert Service Bulletin 145-36-A018, dated April 14, 2000; or EMBRAER Service Bulletin 145-36-0018, dated November 5, 2002; are considered acceptable for compliance with the actions specified in paragraph (f) of this AD.
(h) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, Transport Airplane Directorate, is authorized to approve alternative methods of compliance for this AD.
(i) Unless otherwise specified in this AD, the actions shall be done in accordance with EMBRAER Alert Service Bulletin 145-36-A018, dated April 14, 2000; and EMBRAER Alert Service Bulletin 145-36-A018, Change 01, dated October 20, 2000; as applicable.
(1) The incorporation by reference of EMBRAER Alert Service Bulletin 145-36-A018, Change 01, dated October 20, 2000; is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) The incorporation by reference of EMBRAER Alert Service Bulletin 145-36-A018, dated April 14, 2000; was approved previously by the Director of the Federal Register as of July 3, 2000 (65 FR 39541, June 27, 2000).
(3) Copies may be obtained from Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Note 2: The subject of this AD is addressed in Brazilian airworthiness directive 2000-04-01R2, dated May 28, 2001.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
