[Federal Register Volume 59, Number 219 (Tuesday, November 15, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-27051]
[[Page Unknown]]
[Federal Register: November 15, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-NM-206-AD; Amendment 39-9060; AD 94-22-10]
Airworthiness Directives; de Havilland Model DHC-8-100 and DHC-8-
300 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-8-100 and DHC-8-300 series
airplanes, that requires a revision to the Airplane Flight Manual (AFM)
to advise flight crew members that certain cockpit indications may
reveal faulty anti-collision strobe light units, and to provide
procedures for subsequent flight crew action. This amendment also
requires a modification that eliminates the need for the AFM revision.
This amendment is prompted by reports that the function of the
proximity switch electronics unit (PSEU) may be adversely affected
during operation of the white anti-collision lights. The actions
specified by this AD are intended to ensure correct operation of the
PSEU and its associated systems.
DATES: Effective December 15, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 15, 1994.
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, New York Aircraft Certification
Office, FAA, Engine and Propeller Directorate, 181 South Franklin
Avenue, room 202, Valley Stream, New York 11581; telephone (516) 791-
6427; 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-
100 and DHC-8-300 series airplanes was published in the Federal
Register on APRIL 4, 1994 (59 FR 15873). That action proposed to
require a revision to the Airplane Flight Manual (AFM) to advise flight
crew members that certain cockpit indications may reveal faulty anti-
collision strobe light units, and to provide procedures for subsequent
flight crew action. It also proposed to require a modification that
eliminates the need for the AFM revision.
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 proposal be revised to permit
accomplishment of the modification in accordance with later revisions
of the referenced service bulletin that may be approved in the future
by Transport Canada. The commenter states that this would allow
operators to use the most current information when performing the
required modification. The FAA does not concur. To include the phrase,
``or later approved revisions,'' in an AD when referring to a service
bulletin, violates Office of the Federal Register (OFR) regulations
regarding approval of materials that are ``incorporated by reference''
in rules. In general terms, these OFR regulations require that either
the service document contents be published as part of the actual AD
language, or that the service document be submitted for approval by the
OFR as ``referenced'' material, in which case it may be only referred
to in the text of an AD. The AD may only refer to the service document
that was actually submitted and approved by the OFR for ``incorporation
by reference.'' In order for operators to use later revisions of the
referenced document (issued after the publication of the AD), either
the AD must be revised to reference the specific later revisions, or
operators must request the approval of them as an alternative method of
compliance with this AD [under the provisions of paragraph (d)].
This same commenter suggests that the proposal be revised to make
only the replacement of the power supplies mandatory, not the
replacement of the strobe light assemblies. The commenter points out
that Modification 8/1273, as would be required by proposed paragraph
(c), requires that both the currently-installed strobe light assembly
and power supply be replaced with a Whelen strobe light assembly and
power supply. The commenter states that (1) the addressed unsafe
condition is known to be caused by a capacitor failure in the Grimes
power supply only, not in the Grimes strobe light assemblies; and (2)
the Whelen power supplies work in conjunction with the Grimes strobe
light assemblies. Therefore, the commenter reasons that only the
replacement of the Grimes power supply is necessary to correct the
unsafe condition, and that the replacement of the light assemblies
should be at the operator's discretion. The FAA does not concur. Both
the Grimes and Whelen anti-collision light systems (including both the
power supply and strobe light assembly) are approved under individual
Technical Standard Orders (TSO), for which de Havilland has compliance
data approved only for the installation of each as an individual
system; currently, there is no compliance data approved for
installation of a ``mixed system'' (i.e., Whelen power supplies with
Grimes strobe light assemblies, or vice versa). In light of this, the
FAA has determined that the complete Grimes system (including both the
power supply and the strobe light assembly) must be replaced with a
complete Whelen system.
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 as proposed.
The FAA estimates that 74 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 16 work hours per
airplane to accomplish the required actions, and that the average labor
rate is $55 per work hour. Required parts for installation of
Modification 8/1273 at all three locations will cost approximately
$1,397 per airplane. Based on these figures, the total cost impact of
the AD on U.S. operators is estimated to be $168,498, or $2,277 per
airplane.
The total cost impact figure discussed above is 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 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:
94-22-10 de Havilland, Inc.: Amendment 39-9060. Docket 93-NM-206-AD.
Applicability: Model DHC-8-102, -103, -302, and -311 series
airplanes, serial numbers 003 through 214 inclusive; on which
Modification 8/1273 (as described in de Havilland Service Bulletin
S/B No. 8-33-19, Revision `A', dated May 31, 1993) has not been
accomplished; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To ensure correct operation of the proximity switch electronics
unit (PSEU) and its associated systems, accomplish the following:
(a) Within 30 days after the effective date of this AD, revise
the Limitations Section of the FAA-approved Airplane Flight Manual
(AFM) to include the following statement. This may be accomplished
by inserting a copy of this AD into the AFM.
``The electrical power supplies for the white anti-collision
lights may fail and cause the following abnormalities:
--flashing of the landing gear green locked down advisory lights
during cruise;
--fluctuation of cabin pressurization rate needle during cruise; and
--retraction and extension of roll and ground spoilers during ground
operation.
The failure may also result in loss of nose landing gear
steering subsequent to landing, and loss of wheel brakes below 35-40
knots.
If any of these abnormal indications are observed, select A/COL
light switch-RED. Leave the switch in this position for the
remainder of the flight.''
(b) If the flight crew reports the occurrence of any of the
cockpit indications stated in paragraph (a) of this AD: Prior to the
next flight, perform the maintenance procedures to confirm and
isolate the faulty power supply unit, in accordance with paragraph
III., Part B, Accomplishment Instructions of de Havilland Alert
Service Bulletin S.B. A8-33-33, dated May 31, 1993.
(1) If any power supply unit is determined to be faulty, prior
to further flight, replace the unit with a new or serviceable
``Grimes'' unit or a new ``Whelen'' system in accordance with the
alert service bulletin.
(2) If the specific unit causing the faults cannot be
determined, prior to further flight, replace all three units with
new or serviceable ``Grimes'' units or a new ``Whelen'' system in
accordance with the alert service bulletin. Installation of a new
``Whelen'' system at all three locations constitutes terminating
action for the requirements of this AD, and after installation, the
AFM revision required by paragraph (a) of this AD may be removed.
(c) Within 6 months after the effective date of this AD, install
Modification 8/1273 (which entails replacement of the existing anti-
collision strobe lights, brackets, and power supplies with the ``
`Whelen' Anti-Collision Strobe Light System'') at all three
locations, in accordance with de Havilland Service Bulletin S/B No.
8-33-19, Revision ``A'', dated May 31, 1993. Following installation,
the AFM revision required by paragraph (a) of this AD may be
removed.
(d) 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), ANE-170, 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: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(e) 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.
(f) The actions shall be done in accordance with de Havilland
Alert Service Bulletin S.B. A8-33-33, dated May 31, 1993; and de
Havilland Service Bulletin S/B No. 8-33-19, Revision ``A'', dated
May 31, 1993; 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 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.
(g) This amendment becomes effective on December 15, 1994.
Issued in Renton, Washington, on October 26, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-27051 Filed 11-14-94; 8:45 am]
BILLING CODE 4910-13-U
