[Federal Register Volume 63, Number 160 (Wednesday, August 19, 1998)]
[Rules and Regulations]
[Pages 44371-44372]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-21992]
[[Page 44371]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-86-AD; Amendment 39-10714; AD 98-17-12]
RIN 2120-AA64
Airworthiness Directives; British Aerospace (Jetstream) Model
4100 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 British Aerospace (Jetstream) Model 4100 series
airplanes, that requires an eddy current conductivity test to measure
the conductivity of the upper splice plate of the wing, and follow-on
actions, if necessary. 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 correct corrosion of the upper splice plate of the wing, which could
result in reduced structural integrity of the airplane.
DATES: Effective September 23, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 23, 1998.
ADDRESSES: The service information referenced in this AD may be
obtained from AI(R) American Support, Inc., 13850 Mclearen Road,
Herndon, Virginia 20171. 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
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; fax (425) 227-1149.
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 British Aerospace
(Jetstream) Model 4100 airplanes was published in the Federal Register
on April 21, 1998 (63 FR 19680). That action proposed to require an
eddy current conductivity test to measure the conductivity of the upper
splice plate of the wing, and follow-on actions, if necessary.
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.
Issuance of Additional Service Information
Since the issuance of the proposed AD, the manufacturer has issued
British Aerospace Regional Aircraft Service Bulletin J41-57-021, dated
May 7, 1998, which provides service information for replacement of the
upper splice plate of the wing with a new upper splice plate, as
conditionally required by paragraph (b)(1)(ii) of this AD. Although
British Aerospace Regional Aircraft Service Bulletin J41-57-020, dated
March 20, 1997, was referenced in the proposed AD as the appropriate
source of service information for this replacement, the FAA has been
advised that Service Bulletin J41-57-021 provides complete instructions
for accomplishment of the replacement. Paragraph (b)(1)(ii) of the
final rule has been revised to cite Service Bulletin J41-57-021, dated
May 7, 1998, as an additional source of service information for
accomplishment of this action.
Conclusion
After careful review of the available data, the FAA has determined
that air safety and the public interest require the adoption of the
rule with the change described previously. The FAA has determined that
this change will neither increase the economic burden on any operator
nor increase the scope of the AD.
Cost Impact
The FAA estimates that 54 airplanes of U.S. registry will be
affected by this AD, and that it will take approximately 1 work hour
per airplane to accomplish the required eddy current conductivity test,
at an average labor rate of $60 per work hour. Based on these figures,
the cost impact of the test required by this AD on U.S. operators is
estimated to be $3,240, or $60 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.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
98-17-12 British Aerospace Regional Aircraft [Formerly Jetstream
Aircraft Limited; British Aerospace (Commercial Aircraft) Limited]:
Amendment 39-10714. Docket 98-NM-86-AD.
Applicability: Jetstream Model 4100 series airplanes,
constructor's numbers 41004 through 41096 inclusive; 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
[[Page 44372]]
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 (c) 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 correct corrosion of the upper splice plate of the
wing, which could result in reduced structural integrity of the
airplane, accomplish the following:
(a) Within 6 months after the effective date of this AD, perform
an eddy current conductivity test to measure the conductivity of the
upper splice plate of the wing, in accordance with British Aerospace
Regional Aircraft Service Bulletin J41-57-019, Revision 1, dated
November 26, 1997. If the conductivity measurement is greater than
or equal to 35.0% of the International Aluminum and Copper Standards
(IACS), no further action is required by this AD.
(b) During the inspection required by paragraph (a) of this AD,
if the conductivity measurement is less than 35.0% of the IACS:
Prior to further flight, use a boroscope to perform a detailed
visual inspection to detect corrosion along the full length of the
upper splice plate of the wing, in accordance with British Aerospace
Regional Aircraft Service Bulletin J41-57-020, dated March 20, 1997.
Thereafter, repeat the inspection at intervals not to exceed 1 year.
(1) During any inspection required by paragraph (b) of this AD,
if any corrosion is detected that is within the allowable limits
specified in British Aerospace Regional Aircraft Service Bulletin
J41-57-020, dated March 20, 1997: Accomplish the actions required by
paragraphs (b)(1)(i) and (b)(1)(ii) of this AD, at the times
specified in those paragraphs.
(i) Prior to further flight, repair the upper splice plate of
the wing in accordance with Appendix 2 of British Aerospace Regional
Aircraft Service Bulletin J41-57-020, dated March 20, 1997. And
(ii) Within 3 years after the detection of corrosion, replace
the upper splice plate of the wing with a new upper splice plate in
accordance with British Aerospace Regional Aircraft Service Bulletin
J41-57-020, dated March 20, 1997; or British Aerospace Regional
Aircraft Service Bulletin J41-57-021, dated May 7, 1998. Such
replacement constitutes terminating action for the requirements of
this AD.
(2) During any inspection required by paragraph (b) of this AD,
if any corrosion is detected that is outside the allowable limits
specified inBritish Aerospace Regional Aircraft Service Bulletin
J41-57-020, dated March 20, 1997: Prior to further flight, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate.
(c) 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, International Branch, ANM-116.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, International Branch, ANM-116.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(d) 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.
(e) Except as provided by paragraph (b)(2) of this AD, the
actions shall be done in accordance with British Aerospace Regional
Aircraft Service Bulletin J41-57-019, Revision 1, dated November 26,
1997, British Aerospace Regional Aircraft Service Bulletin J41-57-
020, dated March 20, 1997, and British Aerospace Regional Aircraft
Service Bulletin J41-57-021, dated May 7, 1998. 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 AI(R) American Support, Inc., 13850 Mclearen Road,
Herndon, Virginia 20171. Copies may be inspected at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; 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 British
airworthiness directive 005-03-97.
(f) This amendment becomes effective on September 23, 1998.
Issued in Renton, Washington, on August 11, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-21992 Filed 8-18-98; 8:45 am]
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