[Federal Register Volume 64, Number 243 (Monday, December 20, 1999)]
[Rules and Regulations]
[Pages 71003-71004]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-32582]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-165-AD; Amendment 39-11470; AD 99-26-11]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-7 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 Bombardier Model DHC-7 series airplanes, that
requires a one-time visual inspection to detect corrosion on the upper
half of the lower longerons on the inboard nacelles; and corrective
actions, if necessary. This AD also requires modification of the upper
and lower longeron halves. 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 detect and correct corrosion in the upper halves of the left and
right hand lower longerons on the inboard nacelles, which could result
in a landing gear failure.
DATES: Effective January 24, 2000.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 24, 2000.
ADDRESSES: The service information referenced in this AD may be
obtained from Bombardier, Inc., Bombardier Regional Aircraft Division,
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 FAA, Engine and Propeller Directorate, New York
Aircraft Certification Office, 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 and Propulsion Branch, ANE-171, FAA, Engine and Propeller
Directorate, New York Aircraft Certification Office, 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) to include an airworthiness
directive (AD) that is applicable to certain Bombardier Model DHC-7
series airplanes was published in the Federal Register on October 14,
1999 (64 FR 55640). That action proposed to require a one-time visual
inspection to detect corrosion on the upper half of the lower longerons
on the inboard nacelles; and corrective actions, if necessary. That
action also proposed to require modification of the upper and lower
longeron halves.
Comments
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
The FAA estimates that 32 airplanes of U.S. registry will be
affected by this AD.
It will take approximately 8 work hours per airplane to accomplish
the required inspection, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the inspection required by
this AD on U.S. operators is estimated to be $15,360, or $480 per
airplane.
It will take approximately 12 work hours per airplane to accomplish
the required modification, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the modification
required by this AD on U.S. operators is estimated to be $23,040, or
$720 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 a substantial direct
effect 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, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
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:
99-26-11 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-11470. Docket 99-NM-165-AD.
Applicability: Model DHC-7 series airplanes, serial numbers 004
through 113 inclusive, except serial numbers 037 and 061,
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 request approval for an
alternative method of compliance in accordance with paragraph (d) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or
[[Page 71004]]
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 detect and correct corrosion in the upper halves of the left
and right hand lower longerons on the inboard nacelles, which could
result in a landing gear failure, accomplish the following:
Inspection
(a) Within 6 months after the effective date of this AD, perform
a visual inspection to detect corrosion on the upper half of the
lower longerons on the inboard nacelles in accordance with
Bombardier Service Bulletin S.B. 7-54-19, Revision `C,' dated April
16, 1999.
Modification
(b) If no corrosion is detected, prior to further flight, modify
the upper and lower longeron halves in accordance with Bombardier
Service Bulletin S.B. 7-54-19, Revision `C,' dated April 16, 1999.
Corrective Action
(c) If any corrosion is detected, prior to further flight,
accomplish the actions specified in paragraph (c)(1) or (c)(2) of
this AD, as applicable, in accordance with Bombardier Service
Bulletin S.B. 7-54-19, Revision `C,' dated April 16, 1999.
(1) For corrosion that is within the limits specified in the
service bulletin: Accomplish the corrective actions specified in the
service bulletin, and perform a fluorescent penetrant inspection or
high frequency eddy current inspection to detect cracks in areas
where corrosion was blended out. The corrective actions and
inspections shall be done in accordance with the service bulletin.
(i) If no crack is detected, prior to further flight, modify the
upper and lower longeron halves in accordance with the service
bulletin.
(ii) If any crack is detected, prior to further flight,
accomplish the actions required by paragraphs (c)(1)(ii)(A) and
(c)(1)(ii)(B) of this AD.
(A) Either replace the longeron with a new longeron in
accordance with the service bulletin, or repair in accordance with a
method approved by either the Manager, New York Aircraft
Certification Office (ACO), FAA, Engine and Propeller Directorate;
or Transport Canada Civil Aviation (or it's delegated agent). For a
repair method to be approved by the Manager, New York ACO, as
required by this paragraph, the Manager's approval letter must
specifically reference this AD.
(B) Modify the upper and lower longeron halves in accordance
with the service bulletin.
(2) For corrosion that exceeds the limits specified in the
service bulletin: Accomplish the actions required in paragraphs
(c)(1)(ii)(A) and (c)(1)(ii)(B) of this AD.
Alternative Methods of Compliance
(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 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.
Special Flight Permits
(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.
Incorporation by Reference
(f) Except at provided by paragraph (c)(1)(ii)(A) of this AD,
the actions shall be done in accordance with Bombardier Service
Bulletin S.B. 7-54-19, Revision `C,' dated April 16, 1999. 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 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, Engine and Propeller Directorate, New York Aircraft
Certification Office, 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.
Note 3: The subject of this AD is addressed in Canadian
airworthiness directive CF-99-07, dated March 15, 1999.
(g) This amendment becomes effective on January 24, 2000.
Issued in Renton, Washington, on December 10, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-32582 Filed 12-17-99; 8:45 am]
BILLING CODE 4910-13-P