[Federal Register Volume 64, Number 112 (Friday, June 11, 1999)]
[Proposed Rules]
[Pages 31520-31523]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-14819]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-40-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 adoption of a new airworthiness
directive (AD) that is applicable to certain Dornier Model 328-100
series airplanes. This proposal would require repetitive tests of the
flight idle backup system of the propeller control system; repetitive
inspections to determine the level of wear of the pins and bushings of
the cam followers on the power lever rods of the engine controls; and
follow-on corrective actions, if necessary. This proposal also would
require eventual replacement of the power lever and condition lever
rods of the engine controls with new, improved parts, which constitutes
terminating action for the repetitive tests and inspections. This
proposal is prompted by issuance of mandatory continuing airworthiness
information by a foreign civil airworthiness authority. The actions
specified by the proposed AD are intended to prevent failure of the
flight idle backup system. In the event of failure of the primary
propeller control system, such failure of the flight idle backup system
could lead to uncommanded movement of the pitch of the propeller blade
to below flight idle and into reverse thrust during flight, and
consequent reduced controllability of the airplane.
DATES: Comments must be received by July 12, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 99-NM-40-AD, 1601 Lind Avenue, SW.,
[[Page 31521]]
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Fairchild Dornier, Dornier Luftfahrt 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: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; 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 notice may be changed in
light of the comments received.
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
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 99-NM-40-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. 99-NM-40-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority
for Germany, notified the FAA that an unsafe condition may exist on
certain Dornier Model 328-100 series airplanes. The LBA advises that it
has received reports indicating that wear has been detected on the cam
followers of the power lever rods of the engine controls. The LBA
further advises that such wear, if not corrected, could lead to failure
of the flight idle backup system. In the event that the pitch control
unit of the primary propeller control system fails, such failure of the
flight idle backup system could lead to uncommanded movement of the
pitch of the propeller blade to below flight idle and into reverse
thrust during flight, and consequent reduced controllability of the
airplane.
Explanation of Relevant Service Information
Dornier has issued Alert Service Bulletin ASB-328-76-024, Revision
1, dated August 5, 1998, which describes procedures for repetitive
tests of the flight idle backup system of the propeller control system;
repetitive detailed visual inspections to determine the level of wear
of the pins and bushings of the cam followers on the power lever rods
of the engine controls; and follow-on corrective actions, if necessary.
The corrective actions include replacement of the power lever rods with
new power lever rods, replacement of the pins and bushings with new
pins and bushings, inspections of the pins and bushings for wear or
looseness, and tests of the flight idle backup system at changed
intervals.
Dornier also has issued Service Bulletin SB-328-76-268, Revision 1,
dated December 9, 1998, which describes procedures for replacement of
the power lever and condition lever rods of the engine controls with
new, improved parts. This replacement eliminates the need for the
repetitive tests of the flight idle backup system and repetitive
inspections of the power lever rods.
Accomplishment of the actions specified in these service bulletins
is intended to adequately address the identified unsafe condition. The
LBA classified these service bulletins as mandatory and issued German
airworthiness directive 1998-344/3, dated February 11, 1999, in order
to assure 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 the FAA informed of
the situation described above. The FAA has 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 require accomplishment of
the actions specified in the service bulletins described previously,
except as discussed below.
Differences Between Proposed Rule and Foreign Service Information
Operators should note that Dornier Alert Service Bulletin ASB-328-
76-024, Revision 1, does not specify corrective actions if any
discrepancy is found while performing the flight idle backup test. This
proposed AD would require repair of any discrepancy to be accomplished
in accordance with a method approved by either the FAA, or the LBA (or
its delegated agent).
Cost Impact
The FAA estimates that 50 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 1 work
hour per airplane to accomplish the proposed test, and that the average
labor rate is $60 per work hour. Based on these figures, the cost
impact of the test proposed by this AD on U.S. operators is estimated
to be $3,000, or $60 per airplane, per test cycle.
It would take approximately 1 work hour per airplane to accomplish
the proposed inspection, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the inspection proposed by
this AD on U.S. operators is estimated to be $3,000, or $60 per
airplane, per inspection cycle.
It would take approximately 10 work hours per airplane to
accomplish the proposed replacement, at an average labor rate of $60
per work hour. Required parts would be provided by the manufacturer at
no cost to the operators. Based on these figures, the cost impact of
the replacement proposed by this AD on U.S. operators is
[[Page 31522]]
estimated to be $30,000, or $600 per airplane.
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.
Regulatory Impact
The regulations proposed herein would not have substantial direct
effects 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, in accordance with Executive Order 12612, it is
determined that this proposal would not have sufficient federalism
implications to warrant the preparation of a Federalism Assessment.
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.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Dornier Luftfahrt GMBH: Docket 99-NM-40-AD.
Applicability: Model 328-100 series airplanes having serial
numbers (S/N) 3005 through 3098 inclusive, and S/N 3100, 3103, 3104,
3106, 3107, 3109, and 3110, on which Dornier Service Bulletin SB-
328-76-268, dated August 11, 1998, or Revision 1, dated December 9,
1998, has not been accomplished; certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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 request approval for an
alternative method of compliance in accordance with paragraph (g) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the flight idle backup system, which, in
the event of failure of the primary propeller control system, could
lead to uncommanded movement of the pitch of the propeller blade to
below flight idle and into reverse thrust during flight, and
consequent reduced controllability of the airplane, accomplish the
following:
Flight Idle Backup Test
(a) Prior to the accumulation of 3,000 total flight hours, or
within 3 days after the effective date of this AD, whichever occurs
later, perform a test of the flight idle backup system of the
propeller control system in accordance with Dornier Alert Service
Bulletin ASB-328-76-024, Revision 1, dated August 5, 1998. If any
discrepancy is detected, prior to further flight, repair in
accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate;
or the Luftfahrt-Bundesamt (LBA) (or its delegated agent). Repeat
the test thereafter at intervals not to exceed 1 day until
accomplishment of the requirements of paragraph (c), (d), (e), or
(f), as applicable.
Inspection of Cam Followers of Power Lever Rods
(b) Prior to the accumulation of 3,000 total flight hours, or
within 7 days after the effective date of this AD, whichever occurs
later, perform a detailed visual inspection to determine the level of
wear of the pins and bushings of the cam followers of the power lever
rods of the engine controls, in accordance with Dornier Alert Service
Bulletin ASB-328-76-024, Revision 1, dated August 5, 1998. Classify the
level of wear for each power lever rod as specified in paragraphs
(b)(1), (b)(2), and (b)(3) and accomplish the requirements of paragraph
(c), (d), or (e) of this AD, as applicable, at the times specified in
that paragraph.
(1) Type A wear: The bushing is worn such that the pin is visible
in one or more locations.
(2) Type B wear: The bushing is worn, but the pin is not visible.
(3) Type C wear: The bushing is not worn.
Corrective Actions
(c) For power lever rods on which Type A wear is detected during
the inspection required by paragraph (b) of this AD: Within 900 flight
hours after accomplishment of that inspection, accomplish the
requirements of paragraph (c)(1) or (c)(2) of this AD in accordance
with Dornier Alert Service Bulletin ASB-328-76-024, Revision 1, dated
August 5, 1998. Accomplishment of paragraph (c)(1) or (c)(2) terminates
the tests required by paragraph (a) of this AD for that power lever rod
only.
(1) Replace the power lever rod with a new power lever rod.
(2) Replace the pins and bushings with new pins and bushings, and
accomplish paragraphs (c)(2)(i) and (c)(2)(ii) of this AD.
(i) Thereafter, accomplish follow-on inspections and corrective
actions (i.e. inspections for wear or looseness of the replaced pins
and bushings), at the times and in accordance with the Accomplishment
Instructions of the alert service bulletin; and,
(ii) Within 900 flight hours after replacement of the pins and
bushings, replace the power lever rod with a new power lever rod.
(d) For power lever rods on which Type B wear is detected during
the inspection required by paragraph (b) of this AD: Thereafter,
accomplish follow-on inspections and corrective actions at the times
and in accordance with the Accomplishment Instructions of Dornier Alert
Service Bulletin ASB-328-76-024, Revision 1, dated August 5, 1998,
until the requirements of paragraph (f) of this AD are accomplished.
(e) For power lever rods on which Type C wear is detected during
the inspection required by paragraph (b) of this AD: Determination of
Type C wear terminates the tests required by paragraph (a) of this AD
for that power lever rod only. Thereafter, accomplish follow-on
inspections and corrective actions at the times and in accordance with
the Accomplishment Instructions of Dornier Alert Service Bulletin ASB-
328-76-024, Revision 1, dated August 5, 1998, until the requirements of
paragraph (f) of this AD are accomplished.
Terminating Action
(f) Within 6 months after the effective date of this AD: Replace
the power lever
[[Page 31523]]
and condition lever rods of the engine controls with new, improved
parts in accordance with Dornier Service Bulletin SB-328-76-268,
Revision 1, dated December 9, 1998. Accomplishment of the replacement
constitutes terminating action for the requirements of this AD.
Note 2: Replacement of the power lever and condition lever rods
accomplished prior to the effective date of this AD in accordance
with Dornier Service Bulletin SB-328-76-268, dated August 11, 1998,
is considered acceptable for compliance with paragraph (f) of this
AD.
Alternative Methods of Compliance
(g) 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, International Branch, ANM-116.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, International Branch, ANM-116.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
Special Flight Permits
(h) 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.
Note 4: The subject of this AD is addressed in German
airworthiness directive 1998-344/3, dated February 11, 1999.
Issued in Renton, Washington, on June 4, 1999.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-14819 Filed 6-10-99; 8:45 am]
BILLING CODE 4910-13-P
