[Federal Register Volume 63, Number 193 (Tuesday, October 6, 1998)]
[Rules and Regulations]
[Pages 53550-53552]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-26391]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-214-AD; Amendment 39-10814; AD 98-21-06]
RIN 2120-AA64
Airworthiness Directives; British Aerospace Model BAe 146-100A, -
200A, and -300A 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 Model BAe 146-100A, -200A, and
-300A series airplanes, that requires either a one-time non-destructive
test (NDT) or a visual inspection for cracking of the fuselage skin in
the vicinity of frame 29 between stringers 12 and 13, and repair, 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 detect and
correct fatigue cracking of the fuselage skin in the specified area,
which could result in reduced structural integrity of the airplane.
DATES: Effective November 10, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 10, 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)
[[Page 53551]]
that is applicable to certain British Aerospace Model BAe 146-100A, -
200A, and -300A series airplanes was published in the Federal Register
on August 13, 1998 (63 FR 43331). That action proposed to require
either a one-time non-destructive test (NDT) or a visual inspection for
cracking of the fuselage skin in the vicinity of frame 29 between
stringers 12 and 13, and repair, 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.
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 23 airplanes of U.S. registry will be
affected by this AD.
For operators that elect to accomplish the visual inspection rather
than the non-destructive test, it will take approximately 6 work hours
per airplane to accomplish it, at an average labor rate of $60 per work
hour. Based on these figures, the cost impact of the required visual
inspection on U.S. operators is estimated to be $360 per airplane.
For operators that elect to accomplish the non-destructive test
rather than the visual inspection, it will take approximately 8 work
hours per airplane to accomplish it, at an average labor rate of $60
per work hour. Based on these figures, the cost impact of the required
non-destructive test on U.S. operators is estimated to be $480 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 adding the following new
airworthiness directive:
98-21-06 British Aerospace Regional Aircraft (Formerly British
Aerospace Regional Aircraft Limited, Avro International Aerospace
Division; British Aerospace, PLC; British Aerospace Commercial
Aircraft Limited): Amendment 39-10814. Docket 98-NM-214-AD.
Applicability: Model BAe 146-100A, -200A, and -300A series
airplanes, as listed in British Aerospace Service Bulletin SB.53-
144, dated April 27, 1998; 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 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 fatigue cracking of the fuselage skin in
the vicinity of frame 29 between stringers 12 and 13, which could
result in reduced structural integrity of the airplane, accomplish
the following:
(a) Perform either a one-time non-destructive test (NDT) or a
one-time detailed visual inspection for cracking of the fuselage
skin in the vicinity of frame 29 between stringers 12 and 13, in
accordance with British Aerospace Service Bulletin SB.53-144, dated
April 27, 1998, at the time specified in paragraph (a)(1), (a)(2),
(a)(3), or (a)(4) of this AD, as applicable.
(1) For airplanes identified in paragraph 1.D.(1)(a) of the
service bulletin: Inspect prior to the accumulation of 12,000 total
flight cycles, or within 1,000 flight cycles after the effective
date of this AD, whichever occurs later.
(2) For airplanes identified in paragraph 1.D.(1)(b) of the
service bulletin: Inspect prior to the accumulation of 16,000 total
flight cycles, or within 1,200 flight cycles after the effective
date of this AD, whichever occurs later.
(3) For airplanes identified in paragraph 1.D.(1)(c) of the
service bulletin: Inspect prior to the accumulation of 13,500 total
flight cycles, or within 1,000 flight cycles after the effective
date of this AD, whichever occurs later.
(4) For airplanes identified in paragraph 1.D.(1)(d) of the
service bulletin: Inspect prior to the accumulation of 22,000 total
flight cycles, or within 1,400 flight cycles after the effective
date of this AD, whichever occurs later.
(b) If no cracking is detected during the inspection required by
paragraph (a) of this AD, no further action is required by this AD.
(c) If any cracking is detected during the inspection required
by paragraph (a) of this AD, prior to further flight, repair in
accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate;
or the Civil Aviation Authority (or its delegated agent).
(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, 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.
(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.
[[Page 53552]]
(f) Except as provided by paragraph (c) of this AD, the actions
shall be done in accordance with British Aerospace Service Bulletin
SB.53-144, dated April 27, 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 005-04-98.
(g) This amendment becomes effective on November 10, 1998.
Issued in Renton, Washington, on September 28, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-26391 Filed 10-5-98; 8:45 am]
BILLING CODE 4910-13-U
