[Federal Register Volume 59, Number 247 (Tuesday, December 27, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-30940]
[[Page Unknown]]
[Federal Register: December 27, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-NM-46-AD; Amendment 39-9098; AD 94-26-02]
Airworthiness Directives; de Havilland Model DHC-8 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 de Havilland Model DHC-8 series airplanes, that
requires repetitive inspections of the passenger service unit (PSU)
printed circuit boards and power supply connectors to detect corrosion
and evidence of overheating; repair or replacement of the circuit
boards or replacement of connectors, if necessary; and eventual
installation of a terminating modification. This amendment is prompted
by reports that certain PSU printed circuit boards and power supply
connectors have overheated in service. The actions specified by this AD
are intended to prevent overheating of the PSU printed circuit board
and power supply connectors, which could lead to a fire in the PSU.
DATES: Effective January 26, 1995. -
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 26, 1995.
ADDRESSES: The service information referenced in this AD may be
obtained from de Havilland, Inc., Garratt Boulevard, Downsview, Ontario
M3K 1Y5, Canada. 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 FAA,
Engine and Propeller Directorate, New York Aircraft Certification
Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York;
or at the Office of the Federal Register, 800 North Capitol Street,
NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Michele Maurer, Aerospace Engineer,
Systems and Equipment Branch, ANE-173, FAA, Engine and Propeller
Directorate, New York Aircraft Certification Office, 181 South Franklin
Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791-
6428; fax (516) 791-9024.
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 de Havilland Model DHC-8
series airplanes was published as a supplemental notice of proposed
rulemaking (NPRM) in the Federal Register on April 29, 1994 (59 FR
22138). That action proposed to require repetitive inspections of the
passenger service unit (PSU) printed circuit boards and power supply
connectors to detect corrosion and evidence of overheating; repair or
replacement of the circuit boards or replacement of connectors, if
necessary; and eventual installation of a modification that would
terminate the required inspections. -
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received. -
One commenter supports the proposal. -
Another commenter requests that the proposed requirement to submit
inspection results to de Havilland be deleted. The commenter states
that, since the proposed rule would require that a terminating action
be accomplished, and since de Havilland has been aware of the addressed
problem for several years, any data supplied to de Havilland through
inspection reports would not shed any new light on the problem. The FAA
concurs. Upon reconsideration of this proposed requirement, the FAA
considers the submission of reports to be unnecessary. Additionally, de
Havilland has advised the FAA that it foresees no future need to
receive such reports. Accordingly, the FAA has revised the final rule
by deleting the reporting requirement. -
This same commenter requests that the compliance time for the
proposed initial inspection be revised to account for new airplanes.
The commenter suggests that new airplanes should not be required to be
inspected for at least 12 months since new. In considering this
comment, the FAA has determined that the applicability of the final
rule must be revised to limit it only to airplanes having serial
numbers 3 through 369, inclusive. Airplanes having serial numbers
higher that 369 were delivered with the equivalent of Modification 8/
1950 (the terminating modification required by this AD) installed. In
light of this, a revision to the final rule to address ``new''
airplanes, as suggested by the commenter, is unnecessary since all of
the affected airplanes have accumulated more than 12 months since new.
-
The FAA has revised the applicability of the final rule to clarify
the specific part numbers of the subject PSU's installed on the
affected airplanes. -
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been added to this final rule to clarify this requirement. -
The FAA has recently reviewed the figures it has used over the past
several years in calculating the economic impact of AD activity. In
order to account for various inflationary costs in the airline
industry, the FAA has determined that it is necessary to increase the
labor rate used in these calculations from $55 per work hour to $60 per
work hour. The economic impact information, below, has been revised to
reflect this increase in the specified hourly labor rate. -
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes previously
described. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD. -
The FAA estimates that 133 airplanes of U.S. registry will be
affected by this AD. -
The required inspections will take approximately 2 work hours per
airplane to accomplish, at an average labor rate of $60 per work hour.
Based on these figures, the total cost impact of the proposed
inspections on U.S. operators is estimated to be $15,960, or $120 per
airplane, per inspection. -
The required terminating modification will require approximately 3
work hours per PSU to accomplish, at an average labor cost of $60 per
work hour. Required parts would cost approximately $62 per PSU. Each
airplane is equipped with between 18 and 26 PSU's. Based on these
figures, the total cost impact of the proposed modification on U.S.
operators is estimated to be $242 per PSU, or between $4,356 and $6,292
per airplane. -
The total 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. However, the
FAA has been advised that the initial inspection has already been
accomplished on approximately 22 airplanes; therefore the future
economic impact of this rule is reduced by at least $2,640.
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
94-26-02 de Havilland, Inc.: Amendment 39-9098. Docket 93-NM-46-AD.
Applicability: Model DHC-8 series airplanes, serial numbers 003
through 369, inclusive; equipped with passenger service units (PSU)
have part numbers 10-1418-1 or -2, or 10-1081-1 through -8;
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 (c) 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
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent overheating of the passenger service unit (PSU)
printed circuit board and power supply connectors, which could lead
to a fire in the PSU, accomplish the following:
(a) Within 300 hours time-in-service after the effective date of
this AD, or within 30 days after the effective date of this AD, or
within 12 months after any previous inspection conducted prior to
the effective date in accordance with this paragraph, whichever
occurs later: Conduct a visual inspection of all PSU printed circuit
boards and power supply connectors to detect corrosion and evidence
of overheating, in accordance with paragraph III. of de Havilland
Alert Service Bulletin S.B. A8-33-30, Revision `A', dated December
18, 1992.
Note 2: The overheat condition referred to in this paragraph is
the discoloration of the printed circuit board around the connector
interfaces, and not the light conformal coating discoloration
resulting from the normal operation of high current devices mounted
on the printed circuit board.
(1) If no corrosion or evidence of overheating is detected,
repeat the inspection at intervals not to exceed 12 months.
(2) If any corrosion or evidence of overheating of the PSU
printed circuit board is detected as a result of any inspection,
prior to further flight, either repair or replace the PSU printed
circuit board in accordance with the service bulletin. Thereafter,
repeat the inspection at intervals not to exceed 12 months.
(3) If any corrosion or evidence of overheating of the power
supply connectors is detected as a result of any inspection, prior
to further flight, replace the affected power supply connector in
accordance with the service bulletin. Thereafter, repeat the
inspection at intervals not to exceed 12 months.
(b) Within 24 months after the effective date of this AD,
install Modification 8/1950 in accordance with de Havilland Service
Bulletin S.B. 8-33-34, dated August 10, 1993. Installation of this
modification constitutes terminating action for the inspections
required by paragraph (a) of this AD.
(c) 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, New York Aircraft Certification
Office (ACO), FAA, Engine and Propeller Directorate. Operators shall
submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, New York ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(d) Special flight permits may be issued in accordance with
Secs. 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.
(e) The inspections shall be done in accordance with de
Havilland Alert Service Bulletin S.B. A8-33-30, Revision `A', dated
December 18, 1992. The modification shall be done in accordance with
de Havilland Service Bulletin S.B. 8-33-34, dated August 10, 1993.
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 de Havilland, Inc., Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller
Directorate, New York Aircraft Certification Office, 181 South
Franklin Avenue, Room 202, Valley Stream, New York; or at the Office
of the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
(f) This amendment becomes effective on January 26, 1995.
Issued in Renton, Washington, on December 12, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-30940 Filed 12-23-94; 8:45 am]
BILLING CODE 4910-13-U
