[Federal Register Volume 61, Number 108 (Tuesday, June 4, 1996)]
[Rules and Regulations]
[Pages 28031-28033]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-13610]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-180-AD; Amendment 39-9641; AD 96-11-17]
RIN 2120-AA64
Airworthiness Directives; Beech (Raytheon) Model BAe 125 Series
1000A and Model Hawker 1000 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 1000A and
Model Hawker 1000 airplanes, that requires a one-time inspection for
adequate clearances between, and damage to, the flap cables and
turnbuckles, airbrakes cables and turnbuckles, and all other flight
control cables and turnbuckles at keel subframe 15A; and various
follow-on actions, if necessary. This amendment is prompted by reports
of chafing due to insufficient clearance between the flaps turnbuckle
and the subframe, and between the airbrakes cable and the subframe. The
actions specified by this AD are intended to prevent such chafing,
which could result in damage to the flaps turnbuckle and the airbrakes
cable, and subsequent fraying or seizing of the flight control cables.
These conditions, if not corrected, could result in restriction or loss
of the flight controls.
DATES: Effective July 9, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 9, 1996.
ADDRESSES: The service information referenced in this AD may be
obtained
[[Page 28032]]
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:
Tim Backman, Aerospace Engineer, Standardization Branch, ANM-113, FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (206) 227-2797; 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 1000A and Model Hawker 1000 airplanes was published in the
Federal Register on March 12, 1996 (61 FR 9959). That action proposed
to require a one-time visual inspection for adequate clearances
between, and/or damage to, the flap cables and turnbuckles, airbrakes
cables and turnbuckles, and all other flight control cables and
turnbuckles at keel subframe 15A (left-and right-hand side); and
various follow-on actions, if necessary.
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.
Changes 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
1000A and Model Hawker 1000 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 and BAe 125 series 1000B airplanes
are approved for operation should consider adopting corrective action
that is similar to that required by this AD, since those airplanes are
similar in design to the affected airplanes.
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 previously
described. 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 25 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 1 work hour 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 $1,500, or $60 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:
96-11-17 Beech Aircraft Corporation (Formerly DeHavilland; Hawker
Siddeley; British Aerospace, PLC; Raytheon Corporate Jets, Inc.):
Amendment 39-9641. Docket 95-NM-180-AD.
Applicability: Model BAe 125 series 1000A and Model Hawker 1000
airplanes, as listed in Hawker Service Bulletin SB.27-168, dated
July 17, 1995; 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: Beech (Raytheon) Model BAe 125 series 800B and BAe 125
series 1000B 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 the Model BAe 125 series 800B and
BAe 125 series 1000B 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 restriction or loss of the flight controls due to
insufficient clearance and resultant chafing and damage to the flaps
cable and/or turnbuckle and the airbrakes cable, accomplish the
following:
(a) Within 6 months after the effective date of this AD: Perform
a one-time detailed visual inspection for adequate working
clearances and for damage of the flap, airbrakes, and other flight
control cables and turnbuckles with the structure at keel subframe
15A (left- and right-hand sides) specified in Hawker Service
Bulletin SB.27-168, dated July 17, 1995. Perform the inspection in
accordance with that service bulletin. The detailed visual
inspection for working clearances shall be conducted for each
affected flight control through its full range of travel.
[[Page 28033]]
(1) If all clearances are within the limits specified in the
service bulletin, and no damage is found: No further action is
required by this AD.
(2) If the clearance for the flaps controls is outside the
limits specified in the service bulletin: Prior to further flight,
accomplish Modification SB 27-168-253705B in accordance with the
service bulletin.
(3) If the clearance for the airbrakes controls is outside the
limits specified in the service bulletin: Prior to further flight,
repair in accordance with the service bulletin.
(4) If any cable is found to be damaged, and the damage exceeds
the limits defined in Chapter 20-10-31 of the Airplane Maintenance
Manual: Prior to further flight, replace the damaged cable with a
new cable in accordance with the service bulletin.
(5) If any turnbuckle, keel subframe, or polythene strip is
found to be damaged: Prior to further flight, repair in accordance
with a method approved by the Manager, Standardization Branch, ANM-
113, FAA, Transport Airplane Directorate.
(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.
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 Hawker Service
Bulletin SB.27-168, dated July 17, 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 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 July 9, 1996.
Issued in Renton, Washington, on May 23, 1996.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-13610 Filed 6-3-96; 8:45 am]
BILLING CODE 4910-13-U
