[Federal Register Volume 59, Number 72 (Thursday, April 14, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-8818]
[[Page Unknown]]
[Federal Register: April 14, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 91-CE-47-AD; Amendment 39-8882; AD 94-08-10]
Airworthiness Directives: de Havilland DHC-6 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 88-13-
11, which currently requires repetitively inspecting both wing main
spar lower cap angles for corrosion, and repairing or replacing any
corroded part. This action retains these inspection and possible repair
or replacement requirements, but eliminates the dual compliance time of
both hours time-in-service (TIS) and calendar time. The Federal
Aviation Administration (FAA) has determined that, since corrosion
occurs regardless of whether the airplane is in service, the best
compliance method for the proposed action is calendar time. The actions
specified by this AD are intended to prevent failure of the wing
structure because of corroded wing main spar lower cap angles.
DATES: Effective June 13, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 13, 1994.
ADDRESSES: Service information that applies to this AD may be obtained
from de Havilland, Inc., 123 Garratt Boulevard, Downsview, Ontario,
Canada, M3K 1Y5. This information may also be examined at the FAA,
Central Region, Office of the Assistant Chief Counsel, Room 1558, 601
E. 12th Street, Kansas City, Missouri 64106; or at the Office of the
Federal Register, 800 North Capitol Street NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Jon Hjelm, Aerospace Engineer, FAA,
New York Aircraft Certification Office, 181 South Franklin Avenue, Room
202, Valley Stream, New York 11581; telephone (516) 791-6220.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations to include an AD that would apply to certain de
Havilland DHC-6 series airplanes was published in the Federal Register
on December 28, 1993 (58 FR 68575). The action proposed to supersede AD
88-13-11 with a new AD that would retain the requirement of
repetitively inspecting both wing main spar lower cap angles for
corrosion, but require these inspections with a compliance method based
solely on calendar time. The proposed actions would be accomplished in
accordance with the Accomplishment Instructions section of de Havilland
Service Bulletin No. 6/492, Revision A, dated October 23, 1987.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. One comment was received in support of
the proposed rule.
After careful review of all available information, the FAA has
determined that air safety and the public interest require the adoption
of the rule as proposed except for minor editorial corrections. The FAA
has determined that these minor corrections will not change the meaning
of the AD nor add any additional burden upon the public than was
already proposed.
The FAA estimates that 169 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 8 workhours per
airplane to accomplish the required initial inspection, and that the
average labor rate is approximately $55 an hour. Based on these
figures, the total cost impact of the AD on U.S. operators is estimated
to be $74,360. This figure does not account for repetitive inspections.
The only difference between this AD and AD 88-13-11, which will be
superseded by this required action, is limiting the compliance method
to only calendar time instead of both calendar time and hours TIS.
Therefore, the required action will not impose any additional cost
impact upon the public than that which is already required by AD 88-13-
11.
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 copy of the final evaluation prepared for this
action is contained in the Rules Docket. A copy of it may be obtained
by contacting 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 14 CFR part
39 of the Federal Aviation Regulations 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 removing AD 88-13-11, Amendment 39-
5960 (53 FR 23755, June 24, 1988), and by adding a new airworthiness
directive to read as follows:
94-08-10 de Havilland: Amendment 39-8882; Docket No. 91-CE-47-AD.
Supersedes AD 88-13-11, Amendment 39-5960.
Applicability: Models DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-
300 airplanes (all serial numbers), certificated in any category.
Compliance: Required initially in accordance with whichever of
the following is applicable, unless already accomplished, and
thereafter at intervals not to exceed 60 calendar months:
Upon the accumulation of 120 calendar months from the
date of manufacture or within the next 3 calendar months after the
effective date of this AD, whichever occurs later;
Upon the accumulation of 120 calendar months after
incorporating Wing Box Replacement Modification No. 6/1630 in
accordance with de Havilland Service Bulletin (SB) No. 6/362,
Revision 1, dated January 18, 1985, or within the next 3 calendar
months after the effective date of this AD, whichever occurs later;
or
Upon the accumulation of 120 calendar months of
original manufacture of wings if used wings have been installed on
the airplane or within the next 3 calendar months after the
effective date of this AD, whichever occurs later.
To prevent failure of the wing structure because of corroded
wing main spar lower cap angles, accomplish the following:
(a) Visually inspect the wing main spar and lower spar cap
extensions for corrosion using a high intensity light in accordance
with paragraph A in the ACCOMPLISHMENT INSTRUCTIONS section of de
Havilland SB No. 6/492, Revision A, dated October 23, 1987.
(b) If corrosion is found during the inspection required by
paragraph (a) of this AD that exceeds the criteria specified in the
COMPLIANCE section of de Havilland SB No. 6/492, Revision A, dated
October 23, 1987, prior to further flight, accomplish the following:
(1) Remove all surface corrosion and replace the cap angles in
accordance with the ACCOMPLISHMENT INSTRUCTIONS section of de
Havilland SB No. 6/492, Revision A, dated October 23, 1987.
(2) Dye penetrant inspect all parts where corrosion was removed
to ensure that the part is corrosion-free. Replace any parts that
have corrosion damage and reprotect reworked areas utilizing
information specified in de Havilland Technical Advisory Bulletin
No. 626/1, dated November 1970.
(c) If any parts are reworked per the inspection result
requirements of this AD, prior to further flight, accomplish the
following:
(1) Submit the details of all reworked areas to the manufacturer
through the New York Aircraft Certification Office (ACO) at the
address specified in paragraph (e) of this AD; and
(2) Incorporate any additional instructions provided by the New
York ACO as a condition for returning the airplane to service.
(d) Special flight permits may be issued in accordance with 14
CFR 21.197 and 21.199 to operate the airplane to a location where
the requirements of this AD can be accomplished.
(e) An alternative method of compliance or adjustment of the
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, New York ACO, FAA,
181 South Franklin Avenue, room 202, Valley Stream, New York 11581.
The request shall be forwarded through an appropriate FAA
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.
(f) The inspections and repair or replacement (as necessary)
required by this AD shall be done in accordance with de Havilland
Service Bulletin No. 6/492, Revision A, dated October 23, 1987. 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., 123 Garratt
Boulevard, Downsview, Ontario, Canada, M3K 1Y5. Copies may be
inspected at the FAA, Central Region, Office of the Assistant Chief
Counsel, room 1558, 601 E. 12th Street, Kansas City, Missouri, or at
the Office of the Federal Register, 800 North Capitol Street NW.,
suite 700, Washington, DC.
(g) This amendment (39-8882) supersedes AD 88-13-11, Amendment
39-5960.
(h) This amendment (39-8882) becomes effective on June 13, 1994.
Issued in Kansas City, Missouri, on April 7, 1994.
Larry D. Malir,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-8818 Filed 4-13-94; 8:45 am]
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