[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