Airworthiness Directives; Raytheon Corporate Jets Model Hawker 800 and 1000 and Model DH/BH/HS/BAe 125 Series Airplanes

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]

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