[Federal Register: April 1, 2004 (Volume 69, Number 63)]
[Proposed Rules]
[Page 17097-17101]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01ap04-26]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-294-AD]
RIN 2120-AA64
Airworthiness Directives; Dornier Model 328-100 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to all Dornier Model 328-100
series airplanes, that currently requires certain revisions to the
airplane flight manual, replacement of certain de-icing boots in the
air intake duct assemblies of the engine with re-designed units,
repetitive inspections of the boots to find discrepancies, and
corrective action if necessary. This action would also require
modification of the engine air inlet de-icing system. This action would
extend the repetitive inspection interval required by the existing AD,
and would add repetitive debonding/delamination and leakage inspections
of the de-icing boots, and corrective action if necessary. Initiation
of the extended repetitive inspections and new repetitive inspections
would end the repetitive inspections required by the existing AD. The
actions specified by the proposed AD are intended to prevent engine
malfunction due to failure of the engine air inlet de-icing system,
which could result in reduced controllability of the airplane. This
action is intended to address the identified unsafe condition.
DATES: Comments must be received by May 3, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-294-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address:
9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2002-NM-294-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 or 2000 or
ASCII text.
The service information referenced in the proposed rule may be
obtained from AvCraft Aerospace GmbH, P.O. Box 1103, D-82230 Wessling,
Germany. This information may be examined at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.
FOR FURTHER INFORMATION CONTACT: Tom Groves, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1503; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the rules docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this action may be changed in
light of the comments received.
Submit comments using the following format:
Organize comments issue-by-issue. For example,
discuss a request to change the compliance time and a request to change
the service bulletin reference as two separate issues.
For each issue, state what specific change to
the proposed AD is being requested.
Include justification (e.g., reasons or data)
for each request.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
[[Page 17098]]
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2002-NM-294-AD.'' The postcard will be date stamped
and returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 2002-NM-294-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On March 14, 1995, the FAA issued AD 95-04-51, amendment 39-9179
(60 FR 15037, March 22, 1995), applicable to all Dornier Model 328-100
series airplanes, to require certain revisions to the airplane flight
manual (AFM), replacement of certain de-icing boots in the air intake
duct assemblies of the engine with re-designed units, and inspections
of the boots to find discrepancies. That action was prompted by reports
of failures of the engine air inlet de-icing system, including
debonding of the boots from the engine air intake ducts, failure of the
air-tight chambers in the boots, and malfunction and subsequent
shutdown of an engine during flight. The requirements of that AD are
intended to prevent engine malfunction due to failure of the engine air
inlet de-icing system.
Actions Since Issuance of Previous Rule
In the preamble to AD 95-04-51, we specified that the actions
required by that AD were considered to be ``interim action'' and that
we may consider further rulemaking action. The manufacturer now has
developed an improved modification of the engine air inlet de-icing
system. We have determined that further rulemaking is necessary to
require the modification on affected airplanes; this proposed AD
follows from that determination.
Explanation of New Service Information
The manufacturer has issued the following Dornier Service
Bulletins:
SB-328-71-122, Revision 1, dated May 10, 1999,
which describes procedures for the modification of the engine air
intake ducts. The service bulletin references Westland Aerospace
Limited Service Bulletin SB-WAL328-71-122, dated September 25, 1995, as
an additional source of service information for accomplishment of the
modification.
SB-328-71-125, Revision 3, dated May 10, 1999,
which describes procedures for modification of the engine air inlet de-
icing system, which includes installation of new, improved engine air
intake ducts, installation of geometrically adapted de-icing boots, and
installation of an improved outlet cover plate of the bypass duct. The
service bulletin also describes procedures for doing detailed visual
and tactile inspections of certain de-icing boots for discrepancies
(flat spots, softness, or other irregularities in concave sections, or
improper sealing), and corrective action if discrepancies are found.
The corrective action includes doing a debonding inspection, as
specified in the airplane maintenance manual, and if the debonded area
is outside the allowable limits, replacing all three de-icing boots
before further flight.
Dornier Service Bulletin SB-328-71-125, Revision 3, also references
Westland Aerospace Limited Service Bulletin SB-WAL328-71-125, Revision
1, dated September 25, 1995, as an additional source of service
information for installation of the cover plate of the bypass duct
outlet.
SB-328-30-432, dated April 26, 2002, which
describes procedures for doing detailed visual and tactile inspections
of the engine air inlet de-icing boots to find discrepancies (flat or
soft spots in concave sections, defects on the de-icing boots, or
improper sealing), and corrective action if discrepancies are found.
The corrective action includes doing a debonding/delamination and
leakage inspection, and replacing any delaminated de-icing boot outside
the allowable bonding limits. The inspections are to be repeated
thereafter at certain intervals.
The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority
for Germany, classified the Dornier service information as mandatory
and issued German airworthiness directives 1995-156/3, dated July 1,
1999; and 2002-256, dated September 5, 2002, to ensure the continued
airworthiness of these airplanes in Germany.
FAA's Conclusions
This airplane model is manufactured in Germany and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the LBA has kept us informed of the
situation described above. We have examined the findings of the LBA,
reviewed all available information, and determined that AD action is
necessary for products of this type design that are certificated for
operation in the United States.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would supersede AD 95-04-51 to
continue to require the revisions to the AFM, replacement of certain
de-icing boots in the air intake duct assemblies of the engine with re-
designed units, and repetitive inspections of the boots to find
discrepancies, and corrective action if necessary. This action also
would require modification of the engine air inlet de-icing system and
would add a new AFM revision which changes the compliance time for the
functional test required by the existing AD. It would also extend the
repetitive inspection interval required by the existing AD, and would
add repetitive debonding/delamination and leakage inspections of the
de-icing boots, and corrective action if necessary. Initiation of the
extended repetitive inspections and debonding/delamination and leakage
inspections would end the repetitive inspections required by the
existing AD. The actions would be required to be accomplished in
accordance with the Dornier service bulletins described previously,
except as discussed below.
Differences Among German Airworthiness Directives, Dornier Service
Bulletins, and Proposed AD
The German airworthiness directives do not contain a requirement
for continued accomplishment of the functional test required by the
existing AD, but this proposed AD does continue to require
accomplishment of the functional test.
German airworthiness directive 2002-256 and Service Bulletin SB-
328-30-432 specify a repetitive interval of 800 flight hours for the
detailed inspection and a debonding/delamination and leakage inspection
of the engine air intake de-icing system specified in paragraph 2.B.2.
of the service bulletin. We have determined that, since paragraph
2.B.1.(1) of the service bulletin specifies the same detailed
inspection at a 60-flight-hour interval, it is not necessary to also
require the detailed inspection at the 800-flight-hour interval.
In addition, this proposed AD would require accomplishment of the
debonding/delamination and leakage inspection described in paragraph
2.B.2.(2) of the service bulletin at intervals not to exceed 400 flight
hours,
[[Page 17099]]
in lieu of every 800 flight hours. We have reviewed the service history
of the U.S.-registered fleet of Model 328-100 series airplanes and have
found that an 800-flight-hour debonding/delamination and leakage
inspection interval would not be sufficient to find progressive inlet
boot delamination/debonding before it reaches a point where it
represents a hazard to the airplane. In developing an appropriate
compliance time for this action, we considered not only the safety
implications and the LBA recommendations, but the manufacturer's
recommendation and the degree of urgency associated with addressing the
subject unsafe condition. In light of all of these factors, we find an
initial compliance time of ``within 400 flight hours after the
effective date of this AD,'' and repetitive intervals not to exceed 400
flight hours after the initial inspection, for doing the proposed
debonding/delamination and leakage inspections to be warranted, in that
those times represent appropriate intervals of time allowable for
affected airplanes to continue to operate without compromising safety.
Although Service Bulletin SB-328-30-432 defines the inspection as
``visual'' and ``touch,'' and SB-328-71-125 defines the inspection as
``detailed visual'' and ``tactile,'' this proposed AD defines that
inspection as a ``detailed'' inspection. In addition, we have changed
all references to a ``detailed visual inspection'' in the existing AD
to ``detailed inspection'' in this proposed AD. A new note has been
added to the proposed AD to define this inspection.
German airworthiness directive 1995-156/3 and Service Bulletin SB-
328-71-125 recommend modification of the air intake/de-icing system
``not later than December 31, 1995,'' and ``weekly'' visual and tactile
inspections. This proposed AD would require the modification within 60
flight hours after the effective date of this AD. When German
airworthiness directive 1995-156/2 was issued on November 2, 1995, we
did not take parallel action because we had previously issued an
alternative method of compliance for the existing AD which approved the
modification of the air intake/de-icing system. We are now requiring
the modification on all airplanes that have not yet been modified.
In addition, although ``weekly'' visual and tactile inspections are
specified in the German airworthiness directive and Service Bulletin
SB-328-71-125, this proposed AD would require only a one-time
inspection after accomplishment of the modification, then repetitive
detailed inspections at intervals not to exceed 60 flight hours and
debonding/delamination and leakage inspections at intervals not to
exceed 400 flight hours, per the procedures specified in Service
Bulletin SB-328-30-432.
Service Bulletin SB-328-30-432 describes procedures for completing
a reporting sheet with inspection results, but this proposed AD does
not include such a requirement.
Work Hour Rate Increase
We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost impact information, below, reflects
this increase in the specified hourly labor rate.
Cost Impact
There are about 53 airplanes of U.S. registry that would be
affected by this proposed AD.
The AFM revision currently required by AD 95-04-51 takes about 1
work hour per airplane to accomplish, at an average labor rate of $65
per work hour. Based on these figures, the cost impact of the currently
required AFM revision is estimated to be $65 per airplane.
The inspections currently required by AD 95-04-51 take about 1 work
hour per airplane to accomplish, at an average labor rate of $65 per
work hour. Based on these figures, the cost impact of the currently
required inspections are estimated to be $65 per airplane, per
inspection cycle.
The replacement currently required by AD 95-04-51 takes about 5
work hours per airplane to accomplish, at an average labor rate of $65
per work hour. Required parts will cost about $55,000 per airplane.
Based on these figures, the cost impact of the currently required
replacement is estimated to be $55,325 per airplane.
The modification proposed in this AD action would take about 10
work hours per airplane to accomplish, at an average labor rate of $65
per work hour. Required parts would be free of charge. Based on these
figures, the cost impact of the proposed modification on U.S. operators
is estimated to be $34,450, or $650 per airplane.
The inspection/debonding/delamination and leakage inspection
proposed in this AD action would take about 1 work hour per airplane to
accomplish, at an average labor rate of $65 per work hour. Based on
these figures, the cost impact of the proposed inspection on U.S.
operators is estimated to be $3,445, or $65 per airplane, per
inspection cycle.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the proposed requirements
of this AD action, and that no operator would accomplish those actions
in the future if this AD were not adopted. The cost impact figures
discussed in AD rulemaking actions represent only the time necessary to
perform the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations proposed herein would not have a substantial direct
effect on the States, on the relationship between the national
Government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, it
is determined that this proposal would not have federalism implications
under Executive Order 13132.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, will not have a significant economic impact,
positive or negative, on a substantial number of small entities under
the criteria of the Regulatory Flexibility Act. A copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (14 CFR part 39) as
follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[[Page 17100]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-9179 (60 FR
15037, March 22, 1995), and by adding a new airworthiness directive
(AD), to read as follows:
Fairchild Dornier GmbH (Formerly Dornier Luftfahrt GmbH): Docket
2002-NM-294-AD. Supersedes AD 95-04-51, Amendment 39-9179.
Applicability: All Model 328-100 airplanes, certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent engine malfunction due to failure of the engine air
inlet de-icing system, which could result in reduced controllability
of the airplane, accomplish the following:
Restatement of Certain Requirements of AD 95-04-01
AFM Revision
(a) For all airplanes: Within 24 hours after April 6, 1995 (the
effective date of AD 95-04-51, amendment 39-9179), 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. Continue to do the
functional test until the AFM revision required by paragraph (e) of
this AD is done.
``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.''
Repetitive Inspections/Corrective Action
(b) For airplanes equipped with air intake duct assemblies
having de-icing boots with part numbers (P/N) 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 April 6, 1995: Perform a detailed
inspection and a tactile inspection of the de-icing boots in the air
intake ducts on the engines to find 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.
Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
(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 and tactile inspections required
by paragraph (b)(1) of this AD thereafter at daily intervals until
accomplishment of the modification required by paragraph (f) of this
AD.
(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/Ns 29S-5D5240-21, -23, and -25, with three new units
having P/Ns 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 April 6, 1995, replace all three de-
icing boots having P/N's 29S-5D5240-21, -23, and -25, with three new
units having P/Ns 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
and tactile inspections and the functional tests required by
paragraphs (c) and (e) 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/Ns 29S-5D5240-211,-231, and -251:
Within 7 days after April 6, 1995, perform a detailed inspection and
a tactile inspection of the de-icing boots in the air intake ducts
on the engines to find 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 and tactile inspections required
by paragraph (c) of this AD thereafter at intervals not to exceed 7
days until accomplishment of the modification required by paragraph
(f) of this AD.
(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/Ns 29S-5D5240-211, -231, and -
251, in accordance with Dornier Alert Service Bulletin ASB-328-71-
006, Revision 1, dated February 16, 1995.
Parts Installation
(d) As of April 6, 1995, no de-icing boot having P/N 29S-5D5240-
21, -23, or -25 shall be installed on any airplane.
New Requirements of This Ad
AFM Revision
(e) Within 24 hours after the effective date of this AD: Revise
the Limitations Section of the AFM to include the following
functional test. This may be accomplished by inserting a copy of
this AD into the AFM. Accomplishment of this paragraph ends the
requirements of paragraph (a)(3) of this AD, and the AFM revision
required by that paragraph may be removed from the AFM.
``Accomplish the following test within 24 hours after the
effective date of this AD. Repeat the test 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
[[Page 17101]]
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 inspections required by paragraph (g) of this AD 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.''
Modification of the Engine Air Intake De-icing System
(f) Within 60 flight hours after the effective date of this AD:
Modify the engine air inlet de-icing system (including a one-time
detailed inspection and a debonding/delamination and leakage
inspection) by doing all the actions (including any applicable
corrective action) per the Accomplishment Instructions of Dornier
Service Bulletin SB-328-71-125, Revision 3; and by doing all the
actions per the Accomplishment Instructions of Dornier Service
Bulletin SB-328-71-122, Revision 1; both dated May 10, 1999. Do any
applicable corrective action before further flight per the
applicable service bulletin.
Note 2:
The de-icing boots approved for installation on the modified
engine inlet assembly are specified in paragraph 3., ``Material
Information,'' of the Accomplishment Instructions of Dornier Service
Bulletin SB-328-30-432, dated April 26, 2002.
Note 3:
Dornier Service Bulletin SB-328-71-122, Revision 1, dated May
10, 1999, references Westland Aerospace Limited Service Bulletin SB-
WAL328-71-122, dated September 25, 1995, as an additional source of
service information for modification of the air intake ducts; and
Dornier Service Bulletin SB-328-71-125, Revision 3, dated May 10,
1999, references SB-WAL328-71-125, Revision 1, dated September 25,
1995, as an additional source of service information for
installation of the cover plate of the bypass duct outlet.
Repetitive Inspections
(g) Within 60 flight hours after accomplishment of paragraph (f)
of this AD: Do a detailed inspection of the engine air inlet de-
icing boots to find discrepancies (including flat or soft spots in
concave sections, defects on the de-icing boots, or improper
sealing), per paragraph 2.B.1. of the Accomplishment Instructions of
Dornier Service Bulletin SB-328-30-432, dated April 26, 2002. Do any
applicable corrective action before further flight per the service
bulletin. Repeat the inspection thereafter at intervals not to
exceed 60 flight hours.
(h) Within 400 flight hours after accomplishment of paragraph
(f) of this AD: Do a debonding/delamination and leakage inspection
of the engine air inlet de-icing boots by doing all the applicable
actions per the Accomplishment Instructions of Dornier Service
Bulletin SB-328-30-432, dated April 26, 2002. Do any applicable
corrective action before further flight per the service bulletin.
Repeat the inspection thereafter at intervals not to exceed 400
flight hours.
(i) Initiation of the repetitive inspections required by
paragraphs (g) and (h) of this AD terminates the repetitive
inspections required by paragraphs (b) and (c) of this AD.
No Reporting Required
(j) Where Dornier Service Bulletin SB-328-30-432, dated April
26, 2002; describes procedures for completing a reporting sheet with
inspection results, this AD does not require that action.
Alternative Methods of Compliance
(k)(1) In accordance with 14 CFR 39.19, the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
is authorized to approve alternative methods of compliance for this
AD.
(2) Alternative methods of compliance, approved previously in
accordance with AD 95-04-51, amendment 39-9179, are not considered
to be approved as alternative methods of compliance with this AD.
Note 4:
The subject of this AD is addressed in German airworthiness
directives 1995-156/3, dated July 1, 1999; and 2002-256, dated
September 5, 2002.
Issued in Renton, Washington, on March 26, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-7303 Filed 3-24-04; 8:45 am]
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