[Federal Register: October 13, 2004 (Volume 69, Number 197)]
[Rules and Regulations]
[Page 60804-60807]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13oc04-6]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-294-AD; Amendment 39-13820; AD 2004-20-15]
RIN 2120-AA64
Airworthiness Directives; Dornier Model 328-100 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes 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
amendment also requires modification of the engine air inlet de-icing
system. This action extends the repetitive inspection interval required
by the existing AD, and adds 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 ends the repetitive inspections required by the
existing AD. The actions specified by this 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: Effective November 17, 2004.
The incorporation by reference of certain publications, as listed
in the regulations, is approved by the Director of the Federal Register
as of November 17, 2004.
The incorporation by reference of certain other publications, as
listed in the regulations, was approved previously by the Director of
the Federal Register as of April 6, 1995 (60 FR 15037, March 22, 1995).
ADDRESSES: The service information referenced in this AD may be
obtained from AvCraft Aerospace GmbH, P.O. Box 1103, D-82230 Wessling,
Germany. This information may be examined at the Federal Aviation
Administration (FAA), Transport Airplane Directorate, Rules Docket,
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.
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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 95-04-51,
amendment 39-9179 (60 FR 15037, March 22, 1995), which is applicable to
all Dornier Model 328-100 series airplanes, was published in the
Federal Register on April 1, 2004 (69 FR 17097). The action proposed 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. The 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. The proposed 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.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been submitted in response to
the proposed AD or on the determination of the cost to the public.
Conclusion
We have determined that air safety and the public interest require
the adoption of the AD as proposed.
Clarification of Inspection
We have updated the definition of the detailed inspection in Note 1
of the AD to reflect our current definition.
Cost Impact
There are about 53 airplanes of U.S. registry that will be affected
by this 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 is 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 required in this AD action will take about 10 work
hours per
[[Page 60805]]
airplane to accomplish, at an average labor rate of $65 per work hour.
Required parts will be free of charge. Based on these figures, the cost
impact of the required modification on U.S. operators is estimated to
be $34,450, or $650 per airplane.
The inspection/debonding/delamination and leakage inspection
required in this AD action will 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 required 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 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 adopted herein will 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 final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
``ADDRESSES.''
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
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),
amendment 39-13820, to read as follows:
2004-20-15 Fairchild Dornier Gmbh (Formerly Dornier Luftfahrt GmbH):
Amendment 39-13820. Docket 2002-NM-294-AD. Supersedes AD 95-04-51,
Amendment 39-9179.
Applicability: All Model 328-100 series 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/Ns) 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/Ns 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:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate.
[[Page 60806]]
Inspection aids such as mirror, magnifying lenses, etc., may be
necessary. Surface cleaning and elaborate 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/Ns 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 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 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.
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.
Incorporation by Reference
(l) Unless otherwise specified in this AD, the actions shall be
done in accordance with the service bulletins listed in Table 1 of
this AD, as applicable:
[[Page 60807]]
Table 1.--Incorporation by Reference
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Service bulletin Revision Date
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Dornier Alert Service 1............... February 16, 1995.
Bulletin ASB-328-71-006.
Dornier Service Bulletin SB- Original........ March 17, 1994.
328-30-020.
Dornier Service Bulletin SB- Original........ April 26, 2002.
328-30-432.
Dornier Service Bulletin SB- 1............... May 10, 1999.
328-71-122.
Dornier Service Bulletin SB- 3............... May 10, 1999.
328-71-125.
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(1) The incorporation by reference of the service bulletins
listed in Table 2 of this AD is approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51:
Table 2.--New Service Bulletins for Incorporation by Reference
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Service bulletin Revision Date
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Dornier Service Bulletin SB- Original........ April 26, 2002.
328-30-432.
Dornier Service Bulletin SB- 1............... May 10, 1999.
328-71-122.
Dornier Service Bulletin SB- 3............... May 10, 1999.
328-71-125.
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(2) The incorporation by reference of the service bulletins
listed in Table 3 of this AD was approved previously by the Director
of the Federal Register as of April 6, 1995 (60 FR 15037, March 22,
1995):
Table 3.--Service Bulletins Previously Incorporated by Reference
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Service bulletin Revision Date
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Dornier Alert Service 1............... February 16, 1995.
Bulletin ASB-328-71-006.
Dornier Service Bulletin SB- Original........ March 17, 1994.
328-30-020.
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(3) Copies may be obtained from AvCraft Aerospace GmbH, P.O. Box
1103, D-82230 Wessling, Germany. 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 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.
Effective Date
(m) This amendment becomes effective on November 17, 2004.
Issued in Renton, Washington, on September 30, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-22562 Filed 10-12-04; 8:45 am]
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