[Federal Register Volume 60, Number 2 (Wednesday, January 4, 1995)]
[Rules and Regulations]
[Pages 330-332]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-50]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-137-AD; Amendment 39-9107; AD 94-26-12]
Airworthiness Directives; Raytheon Corporate Jets Model Hawker
800 and 1000 and Model DH/BH/HS/BAe 125 Series 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 Hawker 800 and 1000
and Model DH/BH/HS/BAe 125 series airplanes, that requires inspections
to detect cracking of the sidestay jack pivots of the main landing
gear, and replacement of the sidestay jack pivot assemblies with new
assemblies. This amendment is prompted by a report of fracturing of a
jack pivot, which resulted in the inability of the main landing gear to
deploy. The actions specified by this AD are intended to prevent a
wheels-up landing.
DATES: Effective February 3, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of February 3, 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)
227-2141; fax (206) 227-1320.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
[[Page 331]] Aviation Regulations (14 CFR part 39) to include an
airworthiness directive (AD) that is applicable to certain Raytheon
Corporate Jets Model Hawker 800 and 1000 and Model DH/BH/HS/BAe 125
series airplanes was published in the Federal Register on September 27,
1994 (49 FR 49217). That action proposed to require inspections to
detect cracking of the sidestay jack pivots of the main landing gear,
and replacement of the sidestay jack pivot assemblies with new
assemblies.
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.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been added to this final rule to clarify this requirement.
In addition, the FAA has recently reviewed the figures it has used
over the past several years 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 from $55 per work
hour to $60 per work hour. The economic impact information, below, has
been revised to reflect this increase in the specified hourly labor
rate.
After careful review of the available data 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.
The FAA estimates that 550 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 6 work hours per
airplane to accomplish the required actions, and that the average labor
rate is $60 per work hour. The FAA has been advised that the
manufacturer plans to provide the required parts at no cost to the
operators. Based on these figures, the total cost impact of the AD on
U.S. operators is estimated to be $198,000, or $360 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:
94-26-12 Raytheon Corporate Jets, Inc. (Formerly De Havilland;
Hawker Siddeley; British Aerospace, plc): Amendment 39-9107. Docket
94-NM-137-AD.
Applicability: Model Hawker 800 and 1000 series airplanes and
Model DH/BH/HS/BAe 125-1A through -1000A 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 use the authority
provided in paragraph (f) 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 the inability of the MLG to deploy and a consequent
wheels-up landing, accomplish the following:
(a) 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, at the latest of the times
specified in paragraphs (a)(1), (a)(2), or (a)(3) of this AD.
(1) Within 28 days after the effective date of this AD; 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) If no cracks are found and the sidestay assembly has been
overhauled prior to the accomplishment of the inspection specified
in paragraph (a) of this AD: Accomplish the requirements of
paragraphs (b)(1) and (b)(2) of this AD in accordance with Raytheon
Corporate Jets Service Bulletin SB 32-233, dated June 24, 1994.
(1) Repeat the inspection required by paragraph (a) of this AD
thereafter at intervals not to exceed 1,000 landings.
(2) Prior to the accumulation of 4,000 total landings on the
jack pivot assembly since the sidestay assembly was last overhauled,
or within 300 landings after the effective date of this AD,
whichever occurs later: Replace the jack pivot assembly with a new
assembly. [[Page 332]] Thereafter, prior to the accumulation of
4,000 landings, remove the jack pivot assembly and replace it with a
new assembly in accordance with the service bulletin.
(c) If no cracks are found and the sidestay assembly has not
been overhauled prior to accomplishment of the inspection required
by paragraph (a) of this AD: 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 assembly in accordance with
Raytheon Corporate Jets Service Bulletin SB 32-233, dated June 24,
1994. Thereafter, prior to the accumulation of 4,000 landings on the
jack pivot assembly, replace it with a new assembly in accordance
with the service bulletin.
(d) If any crack is found that does not exceed the limits
specified in Raytheon Corporate Jets Service Bulletin SB 32-233,
dated June 24, 1994, accomplish the requirements of paragraphs
(d)(1), (d)(2), or (d)(3) of this AD, as applicable, in accordance
with the service bulletin.
(1) For sidestay assemblies that have accumulated 4,000 or more
total landings since new that have been overhauled prior to
accomplishment of the inspection specified in paragraph (a) of this
AD: Accomplish paragraphs (d)(1)(i) and (d)(1)(ii) of this AD.
(i) Repeat the inspection required by paragraph (a) of this AD
thereafter at intervals not to exceed 100 landings.
(ii) Prior to the accumulation of 4,000 total landings on the
jack pivot assembly since the sidestay assembly was last overhauled,
or within 300 landings after the effective date of this AD,
whichever occurs later: Replace the jack pivot assembly with a new
assembly. Thereafter, prior to the accumulation of 4,000 landings on
the jack pivot assembly, replace it with a new assembly in
accordance with the service bulletin.
(2) For any sidestay assemblies that have accumulated 4,000 or
more total landings since new that have not been overhauled:
Accomplish paragraphs (d)(2)(i) and (d)(2)(ii) of this AD.
(i) Repeat the inspection required by paragraph (a) of this AD
thereafter at intervals not to exceed 100 landings.
(ii) Within 300 landings after the effective date of this AD,
replace the jack pivot assembly with a new assembly. Thereafter,
prior to the accumulation of 4,000 landings on the jack pivot
assembly, replace it with a new assembly in accordance with the
service bulletin.
(3) For sidestay assemblies that have accumulated less than
4,000 total landings since new: Accomplish paragraphs (d)(3)(i) and
(d)(3)(ii) of this AD.
(i) Repeat the inspection required by paragraph (a) of this AD
thereafter at intervals not to exceed 100 landings.
(ii) 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 assembly. Thereafter, prior to the accumulation of 4,000
landings on the jack pivot assembly, replace it with a new assembly
in accordance with the service bulletin.
(e) If, during any inspection required by this AD, any crack is
found that exceeds the limits specified in paragraph 2.B.(6)(c) of
the Accomplishment Instructions of Raytheon Corporate Jets Service
Bulletin SB 32-233, dated June 24, 1994: Prior to further flight,
replace the cracked pivot assembly with a new assembly in accordance
with the service bulletin. Thereafter, prior to the accumulation of
4,000 landings on the jack pivot assembly, replace it with a new
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, 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 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.
(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 inspections and replacements shall be done in accordance
with Raytheon Corporate Jets Service Bulletin SB 32-233, dated June
24, 1994. 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.
(i) This amendment becomes effective on February 3, 1995.
Issued in Renton, Washington, on December 21, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-50 Filed 1-3-95; 8:45 am]
BILLING CODE 4910-13-U