[Federal Register Volume 61, Number 112 (Monday, June 10, 1996)]
[Rules and Regulations]
[Pages 29276-29277]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-14229]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-122-AD; Amendment 39-9659; AD 96-12-16]
RIN 2120-AA64
Airworthiness Directives; Beech (Raytheon) Model BAe 125 Series
800A and Model Hawker 800 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 Beech (Raytheon) Model BAe 125 series 800A and
Model Hawker 800 airplanes, that requires modification of the airframe
structure in the lower area of the fuselage aft of the wing rear spar.
For certain airplanes, this amendment also requires a functional test
to determine if a particular bolt fouls the flap control system. This
amendment is prompted by reports of restricted control of the aileron
due to water accumulation that froze in the area around an aileron
pulley located in the lower area of the fuselage aft of the wing rear
spar. The actions specified by this AD are intended to prevent such
water accumulation, which could freeze and result in restricted control
of the ailerons; subsequently, this could reduce the pilot's ability to
initiate roll control during critical phases of flight.
DATES: Effective July 15, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 15, 1996.
ADDRESSES: The service information referenced in this AD may be
obtained from Raytheon Aircraft Co., Manger 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: William Schroeder, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2148; fax (206) 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 Beech (Raytheon) Model BAe
125 series 800A and Model Hawker 800 airplanes was published in the
Federal Register on February 9, 1996 (61 FR 4943). That action proposed
to require modification of the airframe structure in the lower area of
the fuselage aft of the wing rear spar. For certain airplanes, that
action also proposed to require a functional test to determine if a
bolt fouls the flap control system.
No Comments Received
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.
Editorial Changes Made to the Final Rule
The FAA has revised the final rule to correctly designate the
affected airplane models as ``Beech (Raytheon) Model BAe 125 series
800A and Model Hawker 800 airplanes.''
Additionally, a new ``Note 2'' has been added to the final rule to
clarify that airworthiness authorities of countries in which Beech
(Raytheon) Model BAe 125 series 800B airplanes are approved for
operation should consider adopting corrective action that is similar to
that required by this AD. Those airplane models are not certificated
for operation in the United States, but are similar in design to the
affected airplanes and, thus, may be subjected to the same unsafe
condition addressed by this AD.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule with the changes previously described.
The FAA has determined that these changes will
[[Page 29277]]
neither increase the economic burden on any operator nor increase the
scope of the AD.
Cost Impact
The FAA estimates that 163 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 25 work hours per
airplane to accomplish the required actions, and that the average labor
rate is $60 per work hour. Required parts be supplied by the
manufacturer at no cost to the operators. Based on these figures, the
cost impact of the AD on U.S. operators is estimated to be $244,500, or
$1,500 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:
96-12-16 Beech Aircraft Corporation. (Formerly deHavilland;
Hawker Siddeley; British Aerospace, plc; Raytheon Corporate Jets,
Inc.): Amendment 39-9659. Docket 95-NM-122-AD.
Applicability: Model BAe 125 series 800A airplanes (including
military variants C-29A and U-125); and Model Hawker 800 airplanes,
excluding airplanes having constructor's numbers 258079 and 258213;
certificated in any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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.
Note 2: Beech (Raytheon) Model BAe 125 series 800B 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
operations in the United States. Airworthiness authorities of
countries in which the Model BAe 125 series 800B airplanes are
approved for operation should consider adopting corrective action,
applicable to those models, that is similar to the corrective action
required by this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent restricted control of the ailerons, which could
reduce the pilot's ability to initiate roll control during critical
phases of flight, accomplish the following:
(a) For all airplanes, except Model BAe 125 series 800A airplane
having constructor's number 258186: Within 6 months after the
effective date of this AD, modify (including functional test) the
airframe structure in the lower area of the fuselage aft of the wing
rear spar, in accordance with Hawker Service Bulletin SB.53-82-
3566G, Revision 3, December 14, 1995.
(b) For airplanes identified in paragraph (a) of this AD on
which Hawker Modification 253566G has been installed prior to the
effective date of this AD, in accordance with Hawker Service
Bulletin SB.53-82-3566G, dated March 1, 1995, Revision 1, dated
March 14, 1995, or Revision 2, dated May 3, 1995: Within 30 days
after the effective date of this AD, perform a functional test to
determine if a bolt fouls the flap control system, in accordance
with paragraph 2.A.(18) of the Accomplishment Instructions of Hawker
Service Bulletin SB.53-82-3566G, Revision 3, dated December 14,
1995. If any foul is detected, prior to further flight, repair in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113, Transport Airplane Directorate, FAA.
(c) For Model BAe 125 series 800A airplane having constructor's
number 258186: Within 6 months after the effective date of this AD,
modify the airframe structure in the lower area of the fuselage aft
of the wing rear spar, in accordance with Hawker Service Bulletin
SB.53-85-3566D, dated March 10, 1995, or Revision 1, dated May 23,
1995.
(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, Standardization Branch, ANM-113.
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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(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.
(f) For certain airplanes, the modification and functional test
shall be done in accordance with Hawker Service Bulletin SB.53-82-
3566G, Revision 3, dated December 14, 1995. For certain other
airplanes, the modification and functional test shall be done in
accordance with Hawker Service Bulletin SB.53-85-3566D, dated March
10, 1995, or Hawker Service Bulletin SB.53-85-3566D, Revision 1,
dated May 23, 1995. 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 Co., Manger 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.
(g) This amendment becomes effective on July 15, 1996.
Issued in Renton, Washington, on May 31, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-14229 Filed 6-7-96; 8:45 am]
BILLING CODE 4910-13-U
