[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