[Federal Register Volume 64, Number 23 (Thursday, February 4, 1999)]
[Rules and Regulations]
[Pages 5587-5588]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-2497]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 64, No. 23 / Thursday, February 4, 1999 /
Rules and Regulations
[[Page 5587]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-295-AD; Amendment 39-11021; AD 99-03-07]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-7 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all Bombardier Model DHC-7 series airplanes, that
requires removal of all attachment bolts and pre-load indicating (PLI)
washers of the wing-to-fuselage attachment fittings; a one-time visual
inspection to detect corrosion of each attachment bolt; and
installation of new attachment bolts and PLI washers of the wing-to-
fuselage attachment fittings. 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 failure of the attachment bolts of the wing-to-fuselage
attachment fittings due to stress corrosion cracking, which could
result in reduced structural integrity of the airplane.
DATES: Effective March 11, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 11, 1999.
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 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.
FOR FURTHER INFORMATION CONTACT: Serge Napoleon, 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) 256-7512;
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 all Bombardier Model DHC-7 series
airplanes was published in the Federal Register on November 30, 1998
(63 FR 65716). That action proposed to require removal of all
attachment bolts and pre-load indicating (PLI) washers of the wing-to-
fuselage attachment fittings; a one-time visual inspection to detect
corrosion of each attachment bolt; and installation of new attachment
bolts and PLI washers of the wing-to-fuselage attachment fittings.
Conclusion
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.
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 50 Model DHC-7 series airplanes of U.S.
registry will be affected by this AD, that it will take approximately
65 work hours per airplane to accomplish the required actions, and that
the average labor rate is $60 per work hour. Required parts will cost
approximately $3,200 per airplane. Based on these figures, the cost
impact of the AD on U.S. operators is estimated to be $355,000, or
$7,100 per airplane.
The 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.
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.
[[Page 5588]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
99-03-07 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-11021. Docket 98-NM-295-AD.
Applicability: All Model DHC-7 series airplanes, 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 (b) 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 failure of the attachment bolts of the wing-to-
fuselage attachment fittings due to stress corrosion cracking, which
could result in reduced structural integrity of the airplane,
accomplish the following:
(a) Within 12 months after the effective date of this AD,
accomplish the requirements of paragraphs (a)(1), (a)(2), and (a)(3)
of this AD, in accordance with Bombardier Service Bulletin S.B. 7-
57-37, dated August 8, 1997.
(1) Remove all attachment bolts (one at a time) and pre-load
indicating (PLI) washers of the wing-to-fuselage attachment
fittings.
(2) Perform a one-time visual inspection to detect corrosion of
each attachment bolt. If any corrosion is detected, within 10 days
after accomplishing the visual inspection, or within 10 days after
the effective date of this AD, whichever occurs later, submit a
report of the inspection results to Bombardier, Inc., Bombardier
Regional Aircraft Division, Garratt Boulevard, Downsview, Ontario
M3K 1Y5, Canada. Information collection requirements contained in
this regulation have been approved by the Office of Management and
Budget (OMB) under the provisions of the Paperwork Reduction Act of
1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control
Number 2120-0056.
(3) Install new attachment bolts (one at a time) and new PLI
washers of the wing-to-fuselage attachment fittings.
(b) 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.
(c) 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.
(d) The removal, inspection, and installation shall be done in
accordance with Bombardier Service Bulletin S.B. 7-57-37, dated
August 8, 1997. 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 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-98-12, dated June 24, 1998.
(e) This amendment becomes effective on March 11, 1999.
Issued in Renton, Washington, on January 28, 1999.
Dorenda D. Baker,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-2497 Filed 2-3-99; 8:45 am]
BILLING CODE 4910-13-U
