[Federal Register Volume 63, Number 219 (Friday, November 13, 1998)]
[Rules and Regulations]
[Pages 63388-63389]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-30050]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-305-AD; Amendment 39-10878; AD 89-18-07 R1]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model BAe.125, DH.125, BH.125, 
and HS.125 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment revises an existing airworthiness directive 
(AD), applicable to certain Raytheon Model BAe.125, DH.125, BH.125, and 
HS.125 series airplanes, that currently requires inspection of the 
elevator mass balance side plate assembly and spigot for corrosion, and 
repair, if necessary; application of corrosion protection treatment; 
and installation of corrosion resistant Monel rivets in the elevator 
balance weight structure. That AD was prompted by reports of corrosion 
on the elevator mass balance side plate assembly and the balance weight 
spigot. The actions specified by that AD are intended to prevent such 
corrosion damage, which could lead to displacement of the side plate 
and consequent control surface interference and jamming of flight 
controls. This amendment limits the applicability of the existing AD.

DATES: Effective December 18, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 18, 1998.

ADDRESSES: The service information referenced in this AD may be 
obtained from Raytheon Aircraft Company, Manager Service Engineering, 
Hawker Customer Support Department, P.O. Box 85, Wichita, Kansas 67201-
0085. 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: Mark Quam, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2145; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by revising AD 89-18-07, 
amendment 39-6297 (54 FR 33874, August 17, 1989), which is applicable 
to certain Raytheon Model BAe.125, DH.125, BH.125, and HS.125 series 
airplanes, was published in the Federal Register on August 13, 1998 (63 
FR 43338). The action proposed to require inspection of the elevator 
mass balance side plate assembly and spigot for corrosion, and repair, 
if necessary; application of corrosion protection treatment; and 
installation of corrosion resistant Monel rivets in the elevator 
balance weight structure. The action also proposed to limit the 
applicability of the existing AD.

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

    Since the issuance of the existing AD, the FAA has reviewed the 
figures it has used in calculating the economic impact of AD activity. 
In order to account for various inflationary costs in the airline 
industry, the FAA has determined that it is necessary to increase the 
labor rate used in these calculations to $60 per work hour. The cost 
impact information, below, has been revised to reflect this increase in 
the specified hourly labor rate.
    Because this AD merely deletes airplanes from the applicability of 
the

[[Page 63389]]

rule, the AD otherwise adds no additional costs, and requires no 
additional work to be performed by affected operators.
    The FAA estimates that 346 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 10 work hours per 
airplane to accomplish the required actions, 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 $207,600, or $600 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 removing amendment 39-6297 (54 FR 
33874, August 17, 1989), and by adding a new airworthiness directive 
(AD), amendment 39-10878, to read as follows:

89-18-07 R1  Raytheon Aircraft Company (Formerly Beech, Raytheon 
Corporate Jets, British Aerospace, Hawker Siddeley, et al.): 
Amendment 39-10878. Docket 97-NM-305-AD. Revises AD 89-18-07, 
Amendment 39-6297.

    Applicability: Model BAe.125, DH.125, BH.125, and HS.125 series 
airplanes; up to and including series 700; 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 (b) 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.
    Note 2: Raytheon (Beech) Model DH.125-400B, BH.125-400B and -
600B, HS.125-600B and -700B, and BAe 125-800B series airplanes are 
similar in design to the airplanes that are subject to the 
requirements of this AD, and, therefore, also may be subject to the 
unsafe condition addressed by this AD. However, as of the effective 
date of this AD, those models are not type certificated for 
operation in the United States. Airworthiness authorities of 
countries in which those models are approved for operation should 
consider adopting corrective action, applicable to these models, 
that is similar to the corrective action required by this AD.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent control surface interference and jamming of flight 
controls, accomplish the following:
    (a) Within 3 years since the date of airplane manufacture, or 
within 60 days after September 21, 1989 (the effective date of AD 
89-18-07, amendment 39-6297), whichever occurs later, accomplish the 
following:
    (1) Inspect the elevator mass balance weight side plate assembly 
and balance weight spigot for corrosion, in accordance with British 
Aerospace Service Bulletin 27-142, Revision 2, dated June 10, 1987, 
or Revision 3, dated November 13, 1989. Any corrosion detected 
during this inspection must be repaired prior to further flight, in 
accordance with the service bulletin.
    (2) Apply corrosion protection treatment and install Monel 
rivets, part number MS9318-052, or British Standard Specification 
SP88-304 rivets, in the elevator balance weight structure, in 
accordance with British Aerospace Service Bulletin 27-142, Revision 
2, dated June 10, 1987, or Revision 3, dated November 13, 1989.
    (b) 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, Standardization Branch, ANM-113, 
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, 
Standardization Branch, ANM-113.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (c) 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.
    (d) The actions shall be done in accordance with British 
Aerospace Service Bulletin 27-142, Revision 2, dated June 10, 1987, 
or British Aerospace Service Bulletin 27-142, Revision 3, dated 
November 13, 1989, which contains the following list of effective 
pages:

------------------------------------------------------------------------
                                   Revision
           Page No.              level shown       Date shown on page
                                   on page
------------------------------------------------------------------------
1.............................  3............  November 13, 1989.
2.............................  Original.....  May 15, 1987.
3.............................  2............  June 10, 1987.
4.............................  1............  May 21, 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 Raytheon Aircraft Company, Manager 
Service Engineering, Hawker Customer Support Department, P.O. Box 
85, Wichita, Kansas 67201-0085. 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.
    (e) This amendment becomes effective on December 18, 1998.

    Issued in Renton, Washington, on November 3, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-30050 Filed 11-12-98; 8:45 am]
BILLING CODE 4910-13-U