[Federal Register Volume 64, Number 13 (Thursday, January 21, 1999)]
[Rules and Regulations]
[Pages 3204-3206]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-1183]
[[Page 3204]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-140-AD; Amendment 39-11003; AD 99-02-11]
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 adopts a new airworthiness directive (AD),
applicable to certain Dornier Model 328-100 series airplanes. This
amendment requires repetitive tests to detect internal leakage of
hydraulic fluid within the hydraulic components of the ground spoiler
system and to detect a buildup of pressure in the return line of the
bypass valve, and corrective action, if necessary; installation of
additional hydraulic lines and an additional hydraulic shutoff valve in
the ground spoiler system; and replacement of the valve block of the
ground spoiler system with a new part. This amendment also requires
eventual replacement of the relief restrictor valves of the ground
spoiler system with redesigned parts, which constitutes terminating
action for the repetitive tests. This amendment is prompted by issuance
of mandatory continuing airworthiness information by a foreign civil
airworthiness authority. The actions specified by this AD are intended
to prevent the ground spoilers from unlocking and deploying during
takeoff or in flight, and consequent reduced controllability of the
airplane.
DATES: Effective February 25, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 25, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from FAIRCHILD DORNIER, DORNIER Luftfahrt 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
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Dornier Model 328-100
series airplanes was published in the Federal Register on July 22, 1998
(63 FR 39252). That action proposed to require repetitive tests to
detect internal leakage of hydraulic fluid within the hydraulic
components of the ground spoiler system and to detect a buildup of
pressure in the return line of the bypass valve, and corrective action,
if necessary; installation of additional hydraulic lines and an
additional hydraulic shutoff valve in the ground spoiler system; and
replacement of the valve block of the ground spoiler system with a new
part. That action also proposed to require eventual replacement of the
relief restrictor valves of the ground spoiler system with redesigned
parts, which would constitute terminating action for the repetitive
tests.
Comment Received
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comment received.
One commenter, the manufacturer, expresses no objection to the
proposed AD, but submits comments to inform the FAA that a new
technical solution has been developed in the form of Dornier Service
Bulletin SB-328-29-269, dated July 16, 1998 [which is referenced in the
proposed AD as the appropriate source of service information for
installation of additional hydraulic lines and an additional hydraulic
shutoff valve in the ground spoiler system]. The commenter states that
it has classified this service bulletin as optional, and that the
service bulletin can be incorporated as an alternate means of
compliance to the actions described in Dornier Service Bulletin SB-328-
29-237. The commenter further advises that the Luftfahrt-Bundesamt
(LBA), which is the airworthiness authority for Germany, is considering
amendment of related German airworthiness directive 1998-031 to include
Dornier Service Bulletin SB-328-29-269 as an alternate means of
compliance.
The FAA infers that the commenter is suggesting that Dornier
Service Bulletin SB-328-29-269, dated July 16, 1998, be added to the AD
as an alternative method of compliance. The FAA has reviewed the
service bulletin, and concurs that accomplishment of Dornier Service
Bulletin SB-328-29-269 is an acceptable alternative method of
compliance for the actions required by paragraph (b) of this AD. The
FAA has added a new Note 2 to include this provision in the final rule.
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the change described
previously. The FAA has determined that this change will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
The FAA estimates that 11 airplanes of U.S. registry will be
affected by this AD.
It will take approximately 3 work hours per airplane to accomplish
the required tests, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the tests required by this
AD on U.S. operators is estimated to be $180 per airplane, per test
cycle.
It will take approximately 16 work hours per airplane to accomplish
the required installation, at an average labor rate of $60 per work
hour. Required parts will be supplied by the manufacturer at no cost to
operators. Based on these figures, the cost impact of the installation
required by this AD on U.S. operators is estimated to be $960 per
airplane.
It will take approximately 2 work hours per airplane to accomplish
the required replacement of the relief restrictor valves, at an average
labor rate of $60 per work hour. Required parts will be supplied by the
manufacturer at no cost to operators. Based on these figures, the cost
impact of this replacement required by this AD on U.S. operators is
estimated to be $120 per airplane.
It will take approximately 2 work hours per airplane to accomplish
the required replacement of the valve block, at an average labor rate
of $60 per work hour. Required parts will be supplied by the
manufacturer at no cost to operators. Based on these figures, the cost
impact of this replacement required by this AD on U.S. operators is
estimated to be $120 per airplane.
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
[[Page 3205]]
those actions in the future if this AD were not adopted.
Regulatory Impact
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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
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
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:
99-02-11 Dornier Luftfahrt GMBH: Amendment 39-11003. Docket 98-NM-
140-AD.
Applicability: Model 328-100 series airplanes, certificated in
any category, equipped with active ground spoiler option 040-001; as
listed in the following service bulletins:
Dornier Service Bulletin SB-328-29-220, Revision 1,
dated May 4, 1998;
Dornier Service Bulletin SB-328-29-237, Revision 1,
dated December 17, 1997;
Dornier Service Bulletin SB-328-27-243, Revision 1,
dated December 18, 1997; and
Dornier Service Bulletin SB-328-27-228, Revision 1,
dated December 18, 1997.
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 request approval for an
alternative method of compliance in accordance with paragraph (f) 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 the ground spoilers from unlocking and deploying
during takeoff or in flight, and consequent reduced controllability
of the airplane, accomplish the following:
(a) Prior to the accumulation of 3,000 total flight hours, or
within 300 flight hours after the effective date of this AD,
whichever occurs later: Perform tests to detect internal leakage of
hydraulic fluid within the hydraulic components of the ground
spoiler system and to detect a buildup of pressure in the return
line of the bypass valve, in accordance with Dornier Service
Bulletin SB-328-29-220, dated May 20, 1997, or Dornier Service
Bulletin SB-328-29-220, Revision 1, dated May 4, 1998.
(1) If no discrepancy is detected, repeat the tests thereafter
at intervals not to exceed 3,000 flight hours, until accomplishment
of the replacement required by paragraph (c) of this AD.
(2) If any discrepancy is detected, prior to further flight,
accomplish the replacement required by paragraph (c) of this AD.
(b) Install additional hydraulic lines and an additional
hydraulic shutoff valve in the ground spoiler system, in accordance
with Dornier Service Bulletin SB-328-29-237, Revision 1, dated
December 17, 1997, at the applicable time specified in either
paragraph (b)(1) or (b)(2) of this AD.
(1) For airplanes having serial numbers up to and including
3086, equipped with ground spoiler actuator, part number 1059A0000-
02: Install within 12 months after the effective date of this AD.
(2) For airplanes having serial numbers up to and including
3086, and equipped with ground spoiler actuator, part number
1059A0000-03: Install within 7 days after the effective date of this
AD.
Note 2: Replacement of hydraulic lines and removal of the
hydraulic shutoff valve in accordance with Dornier Service Bulletin
SB-328-29-269, dated July 16, 1998, is an acceptable alternative
method of compliance for the actions required by paragraph (b) of
this AD.
(c) Replace the relief restrictor valves of the ground spoiler
system, part number ZRV87-2, with a redesigned valve having part
number ZRV87-3, in accordance with Dornier Service Bulletin SB-328-
27-243, Revision 1, dated December 18, 1997, at the applicable time
specified in either paragraph (c)(1) or (c)(2) of this AD.
Accomplishment of this replacement constitutes terminating action
for the repetitive tests required by paragraph (a) of this AD.
(1) For airplanes having serial numbers up to and including
3098, equipped with ground spoiler actuator, part number 1059A0000-
02: Replace within 12 months after the effective date of this AD.
(2) For airplanes having serial numbers up to and including
3098, equipped with ground spoiler actuator, part number 1059A0000-
03: Replace within 7 days after the effective date of this AD.
(d) Replace the valve block of the ground spoiler system with a
new part, in accordance with Dornier Service Bulletin SB-328-27-228,
Revision 1, dated December 18, 1997, at the applicable time
specified in either paragraph (d)(1) or (d)(2) of this AD.
(1) For airplanes having serial numbers up to and including
3095, equipped with ground spoiler actuator, part number 1059A0000-
02: Replace within 12 months after the effective date of this AD.
(2) For airplanes having serial numbers up to and including
3095, equipped with ground spoiler actuator, part number 1059A0000-
03: Replace within 7 days after the effective date of this AD.
(e) As of the effective date of this AD, no person shall install
on the ground spoiler system of any airplane, a valve block, part
number 1060A0000-05, or a relief restrictor valve, part number
ZRV87-2.
(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, International Branch, ANM-116, FAA,
Transport Airplane Directorate. 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.
(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 actions shall be done in accordance with Dornier Service
Bulletin SB-328-29-220, dated May 20, 1997; Dornier Service Bulletin
SB-328-29-220, Revision 1, dated May 4, 1998; Dornier Service
Bulletin SB-328-29-237, Revision 1, dated December 17, 1997; Dornier
Service Bulletin SB-328-27-243, Revision 1, dated December 18, 1997;
and Dornier Service Bulletin SB-328-27-228, Revision 1, dated
December 18, 1997, as applicable. 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
FAIRCHILD DORNIER, DORNIER
[[Page 3206]]
Luftfahrt 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 Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
Note 4: The subject of this AD is addressed in German
airworthiness directives 97-189, dated June 19, 1997; 1998-031,
dated January 15, 1998; 1998-046, dated January 29, 1998; and 1997-
331/2, dated March 12, 1998.
(i) This amendment becomes effective on February 25, 1999.
Issued in Renton, Washington, on January 12, 1999.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-1183 Filed 1-20-99; 8:45 am]
BILLING CODE 4910-13-P
