Airworthiness Directives; British Aerospace Model BAe 146 and Avro 146-RJ Series Airplanes

[Federal Register Volume 65, Number 56 (Wednesday, March 22, 2000)]
[Rules and Regulations]
[Pages 15230-15232]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-6330]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-347-AD; Amendment 39-11638; AD 2000-05-28]
RIN 2120-AA64


Airworthiness Directives; British Aerospace Model BAe 146 and 
Avro 146-RJ 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 all British Aerospace Model BAe 146 and Avro 146-RJ 
series airplanes, that requires a one-time inspection to detect 
cracking or corrosion of the forward attachment bolts of the engine 
pylon to wing interface, and corrective action, if necessary. It also 
requires re-installation with re-protected and sealed bolts torqued to 
a lower level. 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 cracking or corrosion of the forward attachment bolts of the 
engine pylon to wing interface, which could result in reduced 
structural integrity of the engine pylon attachment.

DATES: Effective April 26, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 26, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from British Aerospace Regional Aircraft American Support, 
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 all British Aerospace Model BAe 
146 and Avro 146-RJ series airplanes was published in the Federal 
Register on December 15, 1999 (64 FR 69967). That action proposed to 
require a one-time inspection to detect cracking or corrosion of the 
forward attachment bolts of the engine pylon to wing interface, and 
corrective action, if necessary. That action also proposed to require 
re-installation with re-protected and sealed bolts torqued to a lower 
level.

Comments Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request to Revise Cost Impact Information

    One commenter, an operator, requests that the cost impact 
information in the proposed AD be increased from ``20 work hours 
(including removal and reinstallation of the engines)'' to 112 work 
hours. The commenter states that, as an experienced operator, it 
estimates the time necessary to remove and replace just one engine is 
approximately 8 to 10 work hours. The commenter suggests that an 
appropriate estimate for all actions required by the AD is 
approximately 112 work hours, including hours for removal and 
replacement of four engines and the pylon attachment bolts, as well as 
inspection of the bolts and removal of corrosion.
    The FAA partially concurs. The estimate of 20 work hours provided 
in the AD was based on the estimate of work hours specified in British 
Aerospace Service Bulletin SB.54-10, dated September 16, 1999 (which 
was referenced in the proposed AD and cited in this final rule as the 
appropriate source of service information). However, the FAA has 
determined that such an estimate includes only the time required to 
accomplish the inspections required by this AD, and does not include 
the time necessary for removal and reinstallation of all four engines 
or the time for accomplishment of corrective actions if corrosion is 
found. The FAA has revised the cost impact information, below, by 
removing the parenthetical statement indicating that the 20 work hours 
includes engine removal and reinstallation. However, because the 
economic analysis of the AD is limited to the cost of actions actually 
required by the rule, it does not typically include the costs of 
``indirect'' or ``on-condition'' actions, such as hours necessary for 
access and close, or for repairs. Therefore, no further change to the 
cost impact information is necessary.

Request for Alternative Method of Compliance

    The same commenter requests that the proposed AD include a 
provision for the replacement of the pylon attachment bolts with new 
bolts as an alternative to performing the inspection. The commenter 
notes that such a provision is not specified in the referenced service 
bulletin or in the proposed AD, but states that this option should be 
available at the operator's discretion as an alternative method of 
compliance.
    The FAA concurs. The FAA has reviewed the acceptability of the 
proposed alternative method of

[[Page 15231]]

compliance with the manufacturer and with the Civil Aviation Authority 
(CAA), which is the airworthiness authority for the United Kingdom. 
Based on that input, the FAA has determined that replacement of all 
pylon attachments bolts with new bolts is an acceptable alternative to 
performing the inspection required by this AD, provided that the 
installation methods specified in the service bulletin are followed. 
Such installation methods include retorquing the new bolts to a lower 
level, and applying sealant to the bolts. A new paragraph (b) has been 
added to the final rule to provide this alternative as an acceptable 
means of complying with the requirements of this AD.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 35 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 20 work hours per 
airplane to accomplish the required inspection, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $42,000, or 
$1,200 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 a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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:

2000-05-28  British Aerospace Regional Aircraft (Formerly British 
Aerospace Regional Aircraft Limited, Avro International Aerospace 
Division; British Aerospace, PLC; British Aerospace Commercial 
Aircraft Limited): Amendment 39-11638. Docket 99-NM-347-AD.

    Applicability: All Model BAe 146 and Avro 146-RJ 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 (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 detect and correct cracking or corrosion of the forward 
attachment bolts of the engine pylon to wing interface, which could 
result in reduced structural integrity of the engine pylon 
attachment, accomplish the following:

Inspection and Corrective Action

    (a) Within 4 years since date of manufacture, or within 2,000 
flight cycles after the effective date of this AD, whichever occurs 
later: Except as provided by paragraph (b) of this AD, perform 
applicable inspections (dye penetrant, magnetic particle, and 
detailed visual) to detect discrepancies (including damage, 
cracking, and corrosion) of the forward attachment bolts of the 
engine pylon to wing interface on each engine, in accordance with 
British Aerospace Service Bulletin SB.54-10, dated September 16, 
1999. If any discrepancy is detected, prior to further flight, 
perform applicable corrective actions in accordance with the service 
bulletin.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (b) Replacement of all bolts with new bolts in accordance with 
British Aerospace Service Bulletin SB.54-10, dated September 16, 
1999, within the compliance time specified in paragraph (a) of this 
AD, is an acceptable alternative for compliance with the 
requirements of paragraph (a), provided all installation methods 
(including retorquing the bolts at a lower level, and applying 
sealant to the bolts) specified in the service bulletin are 
followed.

Alternative Methods of Compliance

    (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, FAA, 
Transport Airplane Directorate. 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (d) 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)

[[Page 15232]]

to operate the airplane to a location where the requirements of this 
AD can be accomplished.

Incorporation by Reference

    (e) The actions shall be done in accordance with British 
Aerospace Service Bulletin SB.54-10, dated September 16, 1999. 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 British Aerospace Regional Aircraft 
American Support, 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 4: The subject of this AD is addressed in British 
airworthiness directive 006-09-99.

    (f) This amendment becomes effective on April 26, 2000.


    Issued in Renton, Washington, on March 9, 2000.
Franklin Tiangsing,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-6330 Filed 3-21-00; 8:45 am]
BILLING CODE 4910-13-P

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