[Federal Register Volume 61, Number 128 (Tuesday, July 2, 1996)]
[Rules and Regulations]
[Pages 34368-34370]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-16807]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-268-AD; Amendment 39-9685; AD 96-14-03]
RIN 2120-AA64
Airworthiness Directives; de Havilland Model DHC-8-301, -311, and
-315 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 certain de Havilland Model DHC-8-301,--311, and--
315 series airplanes, that currently requires modification of the
airspeed limitations placard and revision of the Airplane Flight Manual
to specify operating at lower airspeeds when the airplane is operating
at full flaps. That action also provides for the optional termination
of the requirements of the AD for certain airplanes. That action was
prompted by a report that incorrect rivets were installed on the
outboard flaps assemblies of these airplanes. The actions specified by
that AD are intended to prevent structural failure of the outboard
flaps of the wings due to the installation of incorrect rivets in the
flap assemblies, which could result in reduced controllability of the
airplane. This new amendment requires the installation of the
previously optional terminating modification on certain airplanes.
DATES: Effective August 6, 1996.
The incorporation by reference of de Havilland Service Bulletin
S.B. 8-57-24, Revision `A', dated September 26, 1995; and DHC-8 Model
301 Flight Manual, PSM 1-83-1A, Flight Manual Revision 57, dated
September 26, 1995; as listed in the regulations, was approved
previously by the Director of the Federal Register as of February 27,
1996 (61 FR 5277, February 12, 1996).
ADDRESSES: Service information referenced in this amendment may be
obtained from Bombardier, Inc., Bombardier Regional Aircraft Division,
Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be
examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or at the FAA, New York Aircraft Certification
Office, Engine and Propeller Directorate, 10 Fifth Street, Third Floor,
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: Franco Pieri, Aerospace Engineer,
Airframe Branch, ANE-171, FAA, New York Aircraft Certification Office,
Engine and Propeller Directorate, 10 Fifth Street, Third Floor, Valley
Stream, New York 11581; telephone (516) 256-7526; fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 95-26-17,
amendment 39-9475 (61 FR 5277, February 12, 1996), which is applicable
to certain de Havilland Model DHC-8-
[[Page 34369]]
301,-311, and-315 series airplanes, was published in the Federal
Register on April 23, 1996 (61 FR 17855).
For Model DHC-8-301 series airplanes, the action proposed to
continue to require modification of the airspeed limitations placard
and revision of the airplane flight manual (AFM) to specify operating
at lower airspeeds when the airplane is operating at full flaps.
For Model DHC-8-311 and-315 series airplanes, the action proposed
to require that the previously optional terminating modification
(Modification 8/2066) be installed within two years. Once that
modification is installed, the currently-required airspeed limitations
placard and AFM revision may be removed. Additionally, the action
proposed to require that Modification 8/2066 be installed on certain
outboard flap assemblies prior to their installation on these
airplanes.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Cost Impact
There are approximately 18 de Havilland Model DHC-8-301,-311, and-
315 series airplanes of U.S. registry that will be affected by this
proposed AD.
The actions that are currently required by AD 95-26-17
(modification of the airspeed limitations placard and revision of the
Airplane Flight Manual) affect all 18 U.S.-registered airplanes. Those
actions take approximately .5 work hour per airplane to accomplish, at
an average labor rate of $60 per work hour. The cost of required parts
is negligible. Based on these figures, the cost impact on U.S.
operators of the actions currently required is estimated to be $540, or
$30 per airplane.
The new actions that are required by this new AD (installation of
the terminating modification) will affect 14 U.S.-registered Model DHC-
8-311 and-315 series airplanes. The required actions will take
approximately 60 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will be provided by the
manufacturer at no cost to operators. Based on these figures, the cost
impact on U.S. operators of the new requirements of this AD is
estimated to be $50,400, or $3,600 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 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 removing amendment 39-9475 (61 FR
5277, February 12, 1996), and by adding a new airworthiness directive
(AD), amendment 39-9685, to read as follows:
96-14-03 de Havilland, Inc.: Amendment 39-9685. Docket 95-NM-268-AD.
Supersedes AD 95-26-17, Amendment 39-9475.
Applicability: Model DHC-8-301, -311, and -315 series airplanes;
as listed in de Havilland Service Bulletin S.B. 8-57-24, Revision
`A', dated September 26, 1995; 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 (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 structural failure of the outboard flaps of the wings
due to the installation of incorrect rivets in the flap assemblies,
which could result in reduced controllability of the airplane,
accomplish the following:
(a) Within 30 days after February 27, 1996 (the effective date
of AD 95-26-17, amendment 39-9475), accomplish the modification of
the airspeed limitation placards (Modification 8/2498) in accordance
with de Havilland Service Bulletin S.B. 8-57-24, Revision `A', dated
September 26, 1995.
(b) Prior to further flight following accomplishment of the
modification required by paragraph (a) of this AD, revise the
Limitations Section of the FAA-approved Airplane Flight Manual (AFM)
by accomplishing either paragraph (b)(1) or (b)(2) of this AD, as
applicable; and operate the airplane in accordance with those
limitations.
(1) For Model DHC-8-301 series airplanes: Include the
information specified in DHC-8 Model 301 Flight Manual, PSM 1-83-1A,
Flight Manual Revision 57, dated September 26, 1995, which specifies
a lower airspeed limitation at full flaps. This may be accomplished
by inserting a copy of Flight Manual Revision 57 into the AFM.
(2) For Model DHC-8-311 and -315 series airplanes: Include the
following statement in section 2, paragraph 2.4.1.2., of the AFM.
This may be accomplished by inserting a copy of this AD in the AFM.
``Flap extended speed (VFE): Flaps 35 degrees 130 knots
IAS''
(c) For Model DHC-8-311 and -315 series airplanes: Within 2
years after the effective date of this AD, install Modification 8/
2066 in accordance with de Havilland Service Bulletin S.B. 8-57-24,
Revision `A', dated September 26, 1995. Such installation
constitutes terminating action for the
[[Page 34370]]
requirements of paragraphs (a) and (b) of this AD. Following
accomplishment of Modification 8/2066, the airspeed limitations
placard (Modification 8/2498) required by paragraph (a) of this AD
and the AFM limitation required by paragraph (b) of this AD may be
removed.
(d) Except as required by paragraph (e) of this AD: As of
February 27, 1996 (the effective date of AD 95-26-17, amendment 39-
9475), Modification 8/2498 must be accomplished in accordance with
de Havilland Service Bulletin S.B. 8-57-24, Revision `A', dated
September 26, 1995, prior to installation of any outboard flap
assembly having a part number and serial number that is listed in de
Havilland Service Bulletin S.B. 8-57-24, Revision `A', dated
September 26, 1995.
(e) For Model DHC-8-311 and -315 series airplanes: As of two
years after the effective date of this AD, prior to the installation
of any outboard flap assembly having a part number and serial number
that is listed in de Havilland Service Bulletin S.B. 8-57-24,
Revision `A', dated September 26, 1995, install Modification 8/2066
on the affected flap assembly in accordance with that service
bulletin. Installation of this modification terminates the
requirements specified in paragraphs (a), (b), and (d) of this AD.
(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, 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(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 modifications shall be done in accordance with de
Havilland Service Bulletin S.B. 8-57-24, Revision `A', dated
September 26, 1995. The AFM revision may be done in accordance with
DHC-8 Model 301 Flight Manual, PSM 1-83-1A, Flight Manual Revision
57, dated September 26, 1995. The incorporation by reference of
these two documents was approved previously by the Director of the
Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part
51, as of February 27, 1996 (61 FR 5277, February 12, 1996). Copies
may be obtained from Bombardier, Inc., Bombardier Regional Aircraft
Division, 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, New York
Aircraft Certification Office, Engine and Propeller Directorate, 10
Fifth Street, Third Floor, Valley Stream, New York; or at the Office
of the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
(i) This amendment becomes effective on August 6, 1996.
Issued in Renton, Washington, on June 26, 1996.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-16807 Filed 7-1-96; 8:45 am]
BILLING CODE 4910-13-U
