[Federal Register Volume 60, Number 141 (Monday, July 24, 1995)]
[Rules and Regulations]
[Pages 37822-37825]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-17033]
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[[Page 37823]]
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-NM-105-AD; Amendment 39-9307; AD 95-15-04]
Airworthiness Directives; Raytheon Corporate Jets Model BAe 125-
800A and -1000A 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 Raytheon Corporate Jets Model BAe 125-800A and -
1000A airplanes, that requires inspections to detect corrosion of the
wing leading edge skins, including the wing anti-ice fluid distribution
panel (TKS panel) rebate and radius; repair, if necessary; and
subsequent corrosion protection treatment. This amendment also requires
inspections and treatments of the landing/taxiing lamp window assembly
recess and stall vane spoiler rebate/radius. This amendment is prompted
by reports of corrosion of the wing leading edge skin at the interface
with the TKS panels. The actions specified by this AD are intended to
prevent reduced structural integrity of the wing leading edge section
at the interface with the TKS panels and stall vane spoilers, which
could adversely affect the flight characteristics of the airplane.
DATES: Effective August 23, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 23, 1995.
ADDRESSES: The service information referenced in this AD may be
obtained from Raytheon Corporate Jets, Inc., 3 Bishops Square Street,
Albans Road West, Hatfield, Hertfordshire, AL109NE, United Kingdom.
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 Raytheon Corporate Jets
Model BAe 125-800A and -1000A airplanes was published as a supplemental
notice of proposed rulemaking (NPRM) in the Federal Register on April
17, 1995 (60 FR 19183). That action proposed to require inspections to
detect corrosion of the wing leading edge skins, including the wing
anti-ice fluid distribution panel (TKS panel) rebate and radius;
repair, if necessary; and subsequent corrosion protection treatment.
That action also proposed to require inspections and treatments of the
landing/taxiing lamp window assembly recess and the stall vane spoiler
rebate/radius.
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.
The FAA has determined that air safety and the public interest require
the adoption of the rule as proposed.
The FAA estimates that 154 Model BAe 125-800A and -1000A airplanes
of U.S. registry will be affected by this AD. It will take
approximately 130 work hours per airplane to accomplish the inspections
and treatment of the wing leading edge skins (including the TKS rebate
and radius) at an average labor rate of $60 per work hour. Based on
these figures, the total cost impact of the AD on U.S. operators is
estimated to be $1,201,200, or $7,800 per airplane.
The total 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.
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-15-04 Raytheon Corporate Jets, Inc. (Formerly DeHavilland, Inc.;
Hawker Siddeley; British Aerospace, PLC): Amendment 39-9307. Docket
93-NM-105-AD.
Applicability: Model BAe 125-800A and -1000A airplanes, as
listed in Raytheon Corporate Jets Service Bulletin S.B. 57-77,
Revision 1, dated October 28, 1993, 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 use the authority
provided in paragraph (c) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent reduced structural integrity of the wing leading edge
skin and wing anti-ice fluid distribution panel (TKS panel)
interface joint, which could adversely affect the flight
characteristics of the airplane, accomplish the following:
(a) Accomplish the actions specified in paragraphs (a)(1),
(a)(2), (a)(3), and (a)(4) of
[[Page 37824]]
this AD within the time schedule indicated in each paragraph, and in
accordance with Corporate Jets Limited Service Bulletin S.B. 57-77,
dated May 20, 1993, or Raytheon Corporate Jets Service Bulletin S.B.
57-77, Revision 1, dated October 28, 1993.
(1) Within 24 months since airplane manufacture, or within 12
months after the effective date of this AD, whichever occurs later,
perform a detailed visual inspection to detect corrosion of the
polished surface of the top and bottom leading edge skins on each
wing, in accordance with either service bulletin.
(i) If any corrosion is detected and that corrosion is within
the limits specified in either service bulletin, prior to further
flight, remove the corrosion in accordance with either service
bulletin.
(ii) If any corrosion is detected and that corrosion exceeds the
limits specified in either service bulletin, prior to further
flight, repair the wing leading edge skins in accordance with a
method approved by the Manager, Standardization Branch, ANM-113,
FAA, Transport Airplane Directorate.
(2) Prior to further flight after accomplishing the actions
required by paragraph (a)(1) of this AD, conduct a detailed visual
inspection to detect corrosion of the wing anti-ice fluid
distribution panel (TKS panel) rebate and radius, on the top and
bottom leading edge skin section on each wing, in accordance with
either service bulletin.
(i) If any corrosion is detected and that corrosion is within
the limits specified in either service bulletin, prior to further
flight, remove the corrosion in accordance with either service
bulletin.
(ii) If any corrosion is detected and that corrosion exceeds the
limits specified in either service bulletin, prior to further
flight, repair in accordance with a method approved by the Manager,
Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate.
(3) Prior to further flight after accomplishing the actions
required by paragraph (a)(2) of this AD, conduct a dye penetrant
inspection to detect corrosion of the TKS panel rebate and radius,
on the top and bottom leading edge skin section on each wing, in
accordance with either service bulletin.
(i) If any corrosion is detected and that corrosion is within
the limits specified in either service bulletin, prior to further
flight, remove the corrosion in accordance with either service
bulletin.
(ii) If any corrosion is detected and that corrosion exceeds the
limits specified in the service bulletin, prior to further flight,
repair in accordance with a method approved by the Manager,
Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate.
(4) Prior to further flight after accomplishing the actions
required by paragraph (a)(3) of this AD, accomplish both of the
following actions in accordance with either service bulletin:
(i) Apply enhanced protective treatment to the TKS panel rebate
and radius, on the top and bottom leading edge skin section on each
wing; and
(ii) Conduct a flight check of the airplane stall warning system
and stall characteristics.
(b) Accomplish the actions specified in paragraphs (b)(1),
(b)(2), and (b)(3) of this AD within the time schedule indicated in
each paragraph, and in accordance with Raytheon Corporate Jets
Service Bulletin S.B. 57-77, Revision 1, dated October 28, 1993:
Note 2: Any inspection specified in paragraph (b)(1), (b)(2),
and (b)(3) of this AD that was conducted prior to the effective date
of this AD in accordance with Corporate Jets Limited Service
Bulletin S.B. 57-77, dated May 20, 1993, is considered to be in
compliance with this paragraph.
Note 3: The actions required by paragraph (b) of this AD may be
accomplished in conjunction with the actions required by paragraph
(a) within the compliance time required by paragraph (a).
(1) Within 2 years after the effective date of this AD, conduct
a detailed visual inspection to detect corrosion of the landing/
taxiing lamp window assembly recess and the stall vane spoiler
rebate and radius, on the top and bottom leading edge skin section
on each wing, in accordance with the service bulletin.
(i) If any corrosion is detected and that corrosion is within
the limits specified in either service bulletin, prior to further
flight, remove the corrosion in accordance with the service
bulletin.
(ii) If any corrosion is detected and that corrosion exceeds the
limits specified in either service bulletin, prior to further
flight, repair in accordance with a method approved by the Manager,
Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate.
(2) Prior to further flight after accomplishing the actions
required by paragraph (b)(1) of this AD, conduct a dye penetrant
inspection to detect corrosion of the landing/taxiing lamp window
assembly recess and the stall vane spoiler rebate and radius, on the
top and bottom leading edge skin section on each wing, in accordance
with the service bulletin.
(i) If any corrosion is detected and that corrosion is within
the limits specified in either service bulletin, prior to further
flight, remove the corrosion in accordance with the service
bulletin.
(ii) If any corrosion is detected and that corrosion exceeds the
limits specified in either service bulletin, prior to further
flight, repair in accordance with a method approved by the Manager,
Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate.
(3) Prior to further flight after accomplishing the actions
required by paragraph (b)(2) of this AD, accomplish both of the
following actions in accordance with the service bulletin:
(i) Apply enhanced protective treatment to the landing/taxiing
lamp window assembly recess and the stall vane spoiler rebate and
radius, on the top and bottom leading edge skin section on each
wing; and
(ii) Conduct a flight check of the airplane stall warning system
and stall characteristics.
(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, 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 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(d) 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.
(e) The actions shall be done in accordance with the following
service bulletins, as applicable, which contain the specified
effective pages:
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Service bulletin referenced and Revision level shown on
date- Page No.- page- Date shown on page
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Corporate Jets Limited-........ 1-13-..................... Original-................. May 20, 1993.
S.B. 57-77, May 20, 1993
Raytheon Corporate Jets-....... 1-9, A1-A5-............... 1-........................ Oct. 28, 1993.
S.B. 57-77, Revision 1, October 10-14-.................... Original-................. May 20, 1993.
28, 1993-.
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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 Corporate Jets, Inc., 3 Bishops
Square Street, Albans Road West, Hatfield, Hertfordshire, AL109NE,
United Kingdom. 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.
(f) This amendment becomes effective on August 23, 1995.
[[Page 37825]]
Issued in Renton, Washington, on July 6, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-17033 Filed 7-21-95; 8:45 am]
BILLING CODE 4910-13-U
