AD 95-04-51 SUPERSEDED

95-04-51 DORNIER: Amendment 39-9179. Docket 95-NM-24-AD.
Applicability: All Model 328-100 series airplanes, certificated in any category.

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (f) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair removeany airplane from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously.

To prevent engine malfunction due to failure of the engine air inlet de-icing system, accomplish the following:

(a) For all airplanes: Within 24 hours after the effective date of this AD, accomplish paragraphs (a)(1), (a)(2), and (a)(3) of this AD.

(1) Revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) by inserting the following limitation in the AFM. This may be accomplished by inserting a copy of this AD in the AFM.

"During flight, if the 'ENG DEICE FAIL' electronic indication and caution advisory system
(EICAS) annunciation activates for either engine, flight into known or forecast icing
conditions is prohibited."

(2) Revise the Abnormal Procedures Section of the FAA-approved AFM by removing page 4, dated September 1, 1994, of section 04-12-00, and replacing it with the following. This may be accomplished by inserting a copy of this AD in the AFM.

"1. Icing Conditions Exit immediately.
If unable, land at
nearest suitable
airport."

(3) Revise the Limitations Section of the FAA-approved AFM to include the following functional test. This may be accomplished by inserting a copy of this AD in the AFM.

"Accomplish the following test at the applicable time specified as follows:

"For airplanes equipped with air intake duct assemblies having de-icing boots with part
numbers (P/N's) 29S-5D5240-21, -23, and -25: As of 24 hours after the effective date of
AD 95-04-51, accomplish the functional test prior to each flight.

"For airplanes equipped with air intake duct assemblies having de-icing boots with P/N's
29S-5D5240-211 (inlet lip), -231 (bypass duct), and -251 (aft ramp duct): Accomplish the
functional test within 24 hours after the effective date of AD 95-04-51, and thereafter at
daily intervals.

"Perform a functional test of the de-icing system of the air intake ducts of the left and right
engines to determine the condition of the system, in accordance with the procedures
specified below. Flight crew or maintenance personnel shall perform this test.

FUNCTIONAL TEST OF THE DE-ICING SYSTEM

"With engines running at idle power, display and monitor the 'ICE PROTECT' system page of the electronic indication and caution advisory system (EICAS), select left and right
'ENGINE INTAKE' pushbuttons in ('ON'), for a minimum of 60 seconds. Monitor system
page for normal indications of one complete boot inflation and deflation cycle. Monitor
EICAS for normal messages, and absence of 'ENG DEICE FAIL' caution. After 60
seconds and observation of one complete inflation/deflation cycle, release 'ENGINE
INTAKE' pushbuttons to out ('OFF') position, confirm absence of system page and EICAS
cautions, and deselect 'ICE PROTECT' system page. At completion of check, 'ENGINE
INTAKE'pushbuttons may be turned back on if required for departure.

"If any EICAS 'ENG DEICE FAIL' annunciation is observed, or if system normal inflate and
deflate cycling is not observed: The system shall be considered inoperative. Prior to
further flight, the detailed visual and tactile inspections required by paragraph (b) of AD
95-04-51 must be accomplished.

"If no discrepancy with the de-icing boots is found during these inspections, the de-icing
system may be inoperative for a period of time not to exceed that specified in the DO-328
Master Minimum Equipment List (MMEL). Flight into known or forecast icing conditions
is prohibited."

(b) For airplanes equipped with air intake duct assemblies having de-icing boots with P/N's 29S-5D5240-21, -23, and -25: Accomplish paragraphs (b)(1) and (b)(2) of this AD at the times specified in those paragraphs.

(1) Within 24 hours after the effective date of this AD: Perform a detailed visual inspection and atactile inspection of the de-icing boots in the air intake ducts on the engines to detect flat spots, softness, or other discrepancies, and to ensure that the edges of the de-icing boots are sealed properly, in accordance with Dornier Service Bulletin SB-328-30-020, dated March 17, 1994.

(i) If no discrepancies are found and the edges of the de-icing boots are sealed properly (no debonding between the boot and the intake duct), repeat the detailed visual and tactile inspections required by paragraph (b)(1) of this AD thereafter at daily intervals.

(ii) If any discrepancy is found, or if any edge of a de-icing boot is sealed improperly (debonding between the boots and the intake duct), prior to further flight, replace all three de-icing boots having P/N's 29S-5D5240-21, -23, and -25, with three new units having P/N's 29S-5D5240- 211, -231, and -251, in accordance with the procedures specified in Dornier Alert Service Bulletin ASB- 328-71-006, Revision 1, dated February 16, 1995.

(2) Within 5 days after the effective date of this AD, replace all three de-icing boots having P/N's 29S-5D5240-21, -23, and -25, with three new units having P/N's 29S-5D5240-211, -231, and -251, in accordance with Dornier Alert Service Bulletin ASB-328-71-006, Revision 1, dated February 16, 1995. Following such replacement, perform the detailed visual and tactile inspections and the functional tests required by paragraphs (c) and (a)(3) of this AD, respectively, in accordance with the times and procedures specified in those paragraphs.

(c) For airplanes equipped with air intake duct assemblies having de-icing boots with P/N's 29S-5D5240-211,-231, and -251: Within 7 days after the effective date of this AD, perform a detailed visual inspection and a tactile inspection of the de-icing boots in the air intake ducts on the engines to detect flat spots, softness, or other discrepancies, and to ensure that the edges of the de-icing boots are sealed properly, in accordance with the procedures specified in Dornier Service Bulletin SB-328-30-020, dated March 17, 1994.

(1) If no discrepancies are found and the edges of the de-icing boots are sealed properly (no debonding between the boot and the intake duct): Repeat the detailed visual and tactile inspections required by paragraph (c) of this AD thereafter at intervals not to exceed 7 days.

(2) If any discrepancy is found, or if any edge of a de-icing boot is sealed improperly (debonding between the boots and the intake duct): Prior to further flight, replace all three de-icing boots with three new units having P/N's 29S-5D5240-211, -231, and -251, in accordance with Dornier Alert Service Bulletin ASB-328-71-006, Revision 1, dated February 16, 1995; and accomplish the reporting requirement specified in paragraph (d) of this AD.

(d) For airplanes equipped with air intake duct assemblies having de-icing boots with P/N's 29S-5D5240-211, -231, and -251: Within 10 days after accomplishingany inspection or functional test required by this AD, report findings of any discrepancy to the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, WA 98055-4056; fax (206) 227-1320. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056.

(e) After the effective date of this AD, no de-icing boot having P/N 29S-5D5240-21, -23, or -25 shall be installed on any airplane.

(f) 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, Standardization Branch, ANM-113. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.

(g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

(h) The inspections and replacement shall be done in accordance with Dornier Service Bulletin SB-328-30-020, dated March 17, 1994; and Dornier Alert Service Bulletin ASB-328-71-006, Revision 1, dated February 16, 1995. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Dornier Deutsche Aerospace, P.O. Box 1103, D-82230 Wessling, Federal Republic of Germany. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(i) This amendment becomes effective on April 6, 1995, to all persons except those persons to whom it was made immediately effective by telegraphic AD T95-04-51, issued on February 21, 1995, which contained the requirements of this amendment.