[Federal Register Volume 59, Number 186 (Tuesday, September 27, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-23814]
[[Page Unknown]]
[Federal Register: September 27, 1994]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-NM-137-AD]
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: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new 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.
This proposal would 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. This proposal 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 the proposed AD are intended to prevent a wheels-up landing.
DATES: Comments must be received by November 1, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-137-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Manager Product Support, Customer Support Department,
Raytheon Corporate Jets, Inc., Adams Field, P. O. Box 3356, Little
Rock, Arkansas 72203. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed rule by submitting such written data, views, or arguments as
they may desire. Communications shall identify the Rules Docket number
and be submitted in triplicate to the address specified above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed rule. All
comments submitted will be available, both before and after the closing
date for comments, in the Rules Docket for examination by interested
persons. A report summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 94-NM-137-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules
Docket No. 94-NM-137-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for the United Kingdom, recently notified the FAA that an
unsafe condition may exist on certain Raytheon Corporate Jets Model
Hawker 800 and 1000 and Model DH/BH/HS/BAe 125 series airplanes. The
CAA advises that it has received a report of fracturing of a jack
pivot, which resulted in the inability of the main landing gear (MLG)
to deploy. The cracks are apparently caused by metal fatigue. This
condition, if not corrected, could result in a wheels-up landing.
Raytheon Corporate Jets has issued Service Bulletin SB 32-233,
dated June 24, 1994, which describes procedures for repetitive
inspections to detect cracking of the sidestay jack pivots of the MLG,
and replacement of the sidestay jack pivot assemblies with new
assemblies. The CAA classified this service bulletin as mandatory in
order to assure the continued airworthiness of these airplanes in the
United Kingdom.
This airplane model is manufactured in the United Kingdom and is
type certificated for operation in the United States under the
provisions of Sec. 21.29 of the Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral airworthiness agreement. Pursuant
to this bilateral airworthiness agreement, the CAA has kept the FAA
informed of the situation described above. The FAA has examined the
findings of the CAA, reviewed all available information, and determined
that AD action is necessary for products of this type design that are
certificated for operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would require inspections to
detect cracking of the sidestay jack pivots of the MLG, and replacement
of the sidestay jack pivot assemblies with new assemblies. The actions
would be required to be accomplished in accordance with the service
bulletin described previously.
The referenced service bulletin recommends completion of the
initial inspection within 28 days after the issuance date of the
service bulletin. However, the manufacturer has notified the FAA that
there is a delay in the availability of replacement parts for the
sidestay jack pivot assemblies. The FAA has determined that a
compliance time for the initial inspection within 28 days after the
effective date of the final rule for this action will allow adequate
time for the manufacturer to provide the replacement parts and for
operators to comply with the requirements of this AD.
The FAA estimates that 550 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 6 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $55 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
proposed AD on U.S. operators is estimated to be $181,500, or $330 per
airplane.
The total cost impact figure discussed above is based on
assumptions that no operator has yet accomplished any of the proposed
requirements of this AD action, and that no operator would accomplish
those actions in the future if this AD were not adopted.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Raytheon Corporate Jets, Inc. (Formerly De Havilland; Hawker
Siddley; British Aerospace, PLC): 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.
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. 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 t 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: 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
Secs. 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.
Issued in Renton, Washington, on September 21, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-23814 Filed 9-26-94; 8:45 am]
BILLING CODE 4910-13-U
