[Federal Register Volume 62, Number 23 (Tuesday, February 4, 1997)]
[Rules and Regulations]
[Pages 5143-5145]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-2518]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-258-AD; Amendment 39-9913; AD 97-03-07]
RIN 2120-AA64
Airworthiness Directives; Raytheon Model Hawker 800 and 1000 and
Model DH/BH/HS/BAe 125 Series Airplanes (Including Major Variants C29A,
U125, and U125A Series Airplanes)
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Raytheon Model BAe 125-1A through -1000A
series airplanes and Model Hawker 800 and 1000 airplanes, that
currently requires repetitive inspections to detect fatigue cracking of
the sidestay jack pivots of the main landing gear (MLG), and
replacement of the sidestay jack pivot assemblies with new assemblies.
This amendment adds a requirement to replace the sidestay jack pivot
assemblies with new, improved assemblies; when accomplished, this
replacement would terminate the inspection requirements of the AD. This
amendment also expands the applicability of the existing AD to include
additional airplanes. The actions specified by this AD are intended to
prevent fatigue fracturing of the sidestay jack pivots of the MLG,
which could result in the inability of the MLG to deploy and a
consequent wheels-up landing.
DATES: Effective March 11, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 11, 1997.
The incorporation by reference of Raytheon Corporate Jets Service
Bulletin SB 32-233, dated June 24, 1994, listed in the regulations, was
approved previously by the Director of the Federal Register as of
February 3, 1995 (60 FR 330, January 4, 1995).
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: 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) by superseding AD 94-26-12,
amendment 39-9107 (60 FR 330, January 4, 1995), which is applicable to
certain Raytheon Model BAe 125-1A through -1000A series airplanes and
Model Hawker 800 and 1000 airplanes, was published in the Federal
Register on October 18, 1996 (61 FR 54359). The action proposed to
expand the applicability of the existing AD to include additional
airplanes. It also proposed to require installation of new, improved
sidestay jack pivot assemblies, which would constitute terminating
action for the inspection requirements of this AD.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No
[[Page 5144]]
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
There are approximately 550 Raytheon Model BAe 125-1 through 1000A
series airplanes and Model Hawker 1000 airplanes of U.S. registry that
will be affected by this proposed AD.
The actions that are currently required by AD 94-26-12 take
approximately 6 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. The manufacturer is currently
supplying required parts at no cost to the operators. Based on these
figures, the cost impact of the previously required actions on U.S.
operators is estimated to be $198,000, or $360 per airplane, per
inspection cycle.
The new (replacement) actions that are required by this new AD will
take approximately 4 work hours per airplane to accomplish, at an
average labor rate of $60 per work hour. Required parts will cost
approximately $1,200 per airplane. Based on these figures, the cost
impact of the new requirements of this AD on U.S. operators is
estimated to be $792,000, or $1,440 per airplane.
The cost impact figures discussed above are 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 39-9107 (60 FR
330, January 4, 1995), and by adding a new airworthiness directive
(AD), amendment 39-9913, to read as follows:
97-03-07 Raytheon Aircraft Company (Formerly Beech, Raytheon
Corporate Jets, British Aerospace, Hawker Siddley, et al.):
Amendment 39-9913. Docket 95-NM-258-AD. Supersedes AD 94-26-12,
Amendment 39-9107.
Applicability: Model Hawker 800 and 1000 and Model DH/BH/HS/BAe
125 series airplanes (including major variants C29A, U125, and U125A
series airplanes); equipped with main landing gear (MLG) sidestay
assemblies on which Post-Mod 252091 steel jack pivots have been
installed; 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 (f) 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 Model BAe 125 series 800B and BAe 125-1000B
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 125-1000B
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 the inability of the MLG to deploy and a consequent
wheels-up landing, accomplish the following:
Note 3: Paragraph (a) of this AD restates the requirements of AD
94-26-12. As allowed by the phrase, ``unless accomplished
previously,'' if the initial inspection required by that AD has been
accomplished previously, paragraph (a) of this AD does not require
that initial inspection to be repeated.
(a) For Raytheon Model Hawker 800 and 1000 and Model DH/BH/HS/
BAe 125-1A through -1000A series airplanes equipped with MLG
sidestay assemblies on which Post-Mod 252091 steel jack pivots have
been installed, except for airplanes as specified in paragraph (d)
of this AD: Perform a detailed visual inspection, using a 10X
magnifier, to detect cracking of the sidestay assembly jack pivot of
the left and right MLG, in accordance with Raytheon Corporate Jets
Service Bulletin SB 32-233, dated June 24, 1994; Revision 1, dated
July 8, 1994; or Revision 2, dated July 28, 1995; at the latest of
the times specified in paragraph (a)(1), (a)(2), or (a)(3) of this
AD.
(1) Within 28 days after February 3, 1995 (the effective date of
AD 94-26-12, Amendment 39-9107); or
(2) Prior to the accumulation of 3,000 total landings on the
sidestay assembly since new; or
(3) Prior to the accumulation of 1,000 total landings since
overhaul of the sidestay assembly.
(b) For Raytheon Model Hawker 800 and 1000 and Model DH/BH/HS/
BAe 125-1A through -1000A series airplanes equipped with MLG
sidestay assemblies on which Post-Mod 252091 steel jack pivots (part
numbers 25UM1199A, 25UM1229A, and 258UM87-1A) have been installed
prior to June 24, 1994, except for airplanes as specified in
paragraph (d) of this AD:
(1) If no cracks are found during the inspection required by
paragraph (a) of this AD, and the sidestay assembly has been
overhauled prior to the accomplishment of the inspection, accomplish
the requirements of paragraphs (b)(1) and (b)(2) of this AD at the
times specified.
(i) Repeat the inspection specified in paragraph (a) of this AD
within 1,000 landings after accomplishing the initial inspection,
and thereafter at intervals not to exceed 1,000 landings, in
accordance with Raytheon Corporate Jets Service Bulletin SB 32-233,
dated June 24, 1994; Revision 1, dated July 8, 1994; or Revision 2,
dated July 28, 1995.
(ii) Prior to the accumulation of 4,000 total landings on the
jack pivot assembly since the sidestay assembly was new or last
overhauled, or within 300 landings after the effective date of this
AD, whichever occurs
[[Page 5145]]
later: Replace the jack pivot assembly with a new, improved
assembly, in accordance with Raytheon Corporate Jets Service
Bulletin SB.32-233-3597A, dated July 28, 1995. Accomplishment of
this replacement constitutes terminating action for the inspection
requirements of this AD.
(2) If no cracks are found during the inspection required by
paragraph (a) of this AD, and the sidestay assembly has not been
overhauled prior to accomplishment of that inspection: Prior to the
accumulation of 4,000 total landings on the jack pivot assembly, or
within 300 landings after the effective date of this AD, whichever
occurs later, replace the jack pivot assembly with a new, improved
assembly, in accordance with Raytheon Corporate Jets Service
Bulletin SB 32-233, Revision 2, dated July 28, 1995. Accomplishment
of this replacement constitutes terminating action for the
inspection requirements of this AD.
(c) For Raytheon Model Hawker 800 and 1000 and Model DH/BH/HS/
BAe 125-1A through -1000A series airplanes equipped with MLG
sidestay assemblies on which Post-Mod 252091 steel jack pivots (part
numbers 25UM1199A, 25UM1229A, and 258UM87-1A) have been installed on
June 24, 1994, or later, except for airplanes as specified in
paragraph (d) of this AD: Replace the jack pivot assembly with a
new, improved assembly in accordance with Raytheon Corporate Jets
Service Bulletin SB.32-233-3597A, dated July 28, 1995, at the later
of the times specified in paragraph (c)(1) or (c)(2) of this AD.
Accomplishment of this replacement constitutes terminating action
for the inspection requirements of this AD.
(1) Prior to the accumulation of 2,000 total landings since
installation of Post Mod 252091 steel jack pivots. Or
(2) Within 1,000 landings after the effective date of this AD.
(d) For all Raytheon Model BAe 125 Series 800A C29A, U125, and
Hawker 800 U125A airplanes on which Post Mod 252091 steel jack
pivots (part numbers 25UM1199A, 25UM1229A, and 258UM87-1A) have been
installed: Accomplish paragraphs (d)(1) and (d)(2) of this AD at the
times specified in those paragraphs.
(1) Perform a detailed visual inspection, using a 10X magnifier,
to detect cracking of the sidestay assembly jack pivot of the left-
and right-hand MLG, in accordance with Raytheon Corporate Jets
Service Bulletin SB 32-233, Revision 2, dated July 28, 1995, at the
later of the times specified in paragraph (d)(1)(i) or (d)(1)(ii) of
this AD. Thereafter, repeat this inspection at intervals not to
exceed 200 landings, until the requirements of paragraph (d)(2) of
this AD are accomplished.
(i) Prior to the accumulation of 1,200 total landings since the
installation of a steel jack pivot (Post Mod 252091). Or
(ii) Within 56 days or within 200 landings after the effective
date of this AD, whichever occurs first.
(2) Prior to the accumulation of 2,000 total landings on the
jack pivot, or within 300 landings after the effective date of this
AD, whichever occurs later: Replace the sidestay jack pivot assembly
with a new, improved assembly (part numbers 25UM1335-1A and 25-
8UM173-1A) in accordance with Raytheon Corporate Jets Service
Bulletin SB.32-233-3597A, dated July 28, 1995. Accomplishment of
this replacement constitutes terminating action for the inspection
requirements of this AD.
(e) If any crack is detected during any inspection required by
this AD, replace the sidestay jack pivot assembly with a new,
improved assembly (part numbers 25UM1335-1A and 25-8UM173-1A) in
accordance with Raytheon Corporate Jets Service Bulletin SB.32-233-
3597A, dated July 28, 1995, at the time specified in paragraph
(e)(1) or (e)(2) of this AD, as applicable. Accomplishment of this
replacement constitutes terminating action for the inspection
requirements of this AD.
(1) For airplanes on which a crack is detected that does not
exceed the limits specified in the service bulletin, replace the
assembly at the later of the times specified in paragraph (e)(1)(i)
or (e)(1)(ii) of this AD.
(i) Within 100 landings after the effective date of this AD. Or;
(ii) Within 100 landings after the initial detection of the
cracking.
(2) For airplanes on which a crack is detected that exceeds the
limits specified in the service bulletin, prior to further flight,
replace the assembly in accordance with the service bulletin.
(f) 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, 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.
(g) 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.
(h) The actions shall be done in accordance with the following
Raytheon Corporate Jets service bulletins, which contain the
specified list of 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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SB 32-233, June 24, 1994........ 1-10........................ Original............... June 24, 1994.
SB 32-233 Revision 1, July 8, 1, 2, 5..................... 1...................... July 8, 1994.
1994. 3, 4, 6-10.................. Original............... June 24, 1994.
SB 32-233 Revision 2, July 28, 1-4, 6, 7, 9................ 2...................... July 28, 1995.
1995. 5........................... 1...................... July 8, 1994.
8, 10....................... Original............... June 24, 1994.
SB.32-233-3597A, July 28, 1995.. 1-8......................... Original............... July 28, 1995.
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The incorporation by reference of Raytheon Corporate Jets Service
Bulletin SB 32-233, dated June 24, 1994, was approved previously by
the Director of the Federal Register in accordance with 5 U.S.C.
552(a) and 1 CFR part 51 as of February 3, 1995 (60 FR 330, January
4, 1995). The incorporation by reference of the remainder of the
service documents listed above is 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.
(i) This amendment becomes effective on March 11, 1997.
Issued in Renton, Washington, on January 27, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-2518 Filed 2-3-97; 8:45 am]
BILLING CODE 4910-13-U
