Skip to Content

Proposed Rule

Airworthiness Directives; British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 Airplanes

Document Details

Information about this document as published in the Federal Register.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

This document proposes to adopt a new airworthiness directive (AD) that would apply to all British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 airplanes. This proposed AD would require you to inspect the steering jack piston rod for cracks and replace if necessary; measure the torque setting of the steering jack piston rod end fitting and stop bolt; and measure the thickness of the tab washers. This proposed AD would also require you to calculate a new safe life limit for the steering jack piston rod based on the results of the proposed inspection and the proposed measurements. This proposed AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this proposed AD are intended to detect, correct, and prevent cracks in the steering jack piston rod, which could result in failure of the steering jack piston rod. Such failure could lead to loss of steering control of the airplane during takeoff, landing, and taxi operations.

DATES:

The Federal Aviation Administration (FAA) must receive any comments on this proposed rule on or before February 28, 2003.

ADDRESSES:

Submit comments to FAA, Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 2002-CE-56-AD, 901 Locust, Room Start Printed Page 3833506, Kansas City, Missouri 64106. You may view any comments at this location between 8 a.m. and 4 p.m., Monday through Friday, except Federal holidays. You may also send comments electronically to the following address: 9-ACE-7-Docket@faa.gov. Comments sent electronically must contain “Docket No. 2002-CE-56-AD” in the subject line. If you send comments electronically as attached electronic files, the files must be formatted in Microsoft Word 97 for Windows or ASCII text.

You may get service information that applies to this proposed AD from British Aerospace Regional Aircraft, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland; telephone: (01292) 672345; facsimile: (01292) 671625. You may also view this information at the Rules Docket at the address above.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Comments Invited

How Do I Comment on This Proposed AD?

The FAA invites comments on this proposed rule. You may submit whatever written data, views, or arguments you choose. You need to include the rule's docket number and submit your comments to the address specified under the caption ADDRESSES. We will consider all comments received on or before the closing date. We may amend this proposed rule in light of comments received. Factual information that supports your ideas and suggestions is extremely helpful in evaluating the effectiveness of this proposed AD action and determining whether we need to take additional rulemaking action.

Are There Any Specific Portions of This Proposed AD I Should Pay Attention To?

The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this proposed rule that might suggest a need to modify the proposed rule. You may view all comments we receive before and after the closing date of the proposed rule in the Rules Docket. We will file a report in the Rules Docket that summarizes each contact we have with the public that concerns the substantive parts of this proposed AD.

How Can I Be Sure FAA Receives My Comment?

If you want FAA to acknowledge the receipt of your mailed comments, you must include a self-addressed, stamped postcard. On the postcard, write “Comments to Docket No. 2002-CE-56-AD.” We will date stamp and mail the postcard back to you.

Discussion

What Events Have Caused This Proposed AD?

The Civil Aviation Authority (CAA), which is the airworthiness authority for the United Kingdom, recently notified FAA that an unsafe condition may exist on all British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 airplanes. The CAA reports that the steering jack piston rod failed on one of the affected airplanes while in service. The CAA determined that the failure of the piston rod was caused by fatigue cracking on the piston rod end fitting. Fatigue cracking was caused by applying excessive torque to the steering jack piston rod end fitting during assembly.

The safe life limit for the steering jack piston rod is currently 45,000 ground-air-ground (GAG) cycles. Failure of the above-mentioned steering jack piston rod occurred at 2,132 GAG cycles. Because of the possibility that excessive torque had been applied to the steering jack piston rod during assembly, the safe life limit for this part has been reduced.

What Are the Consequences If the Condition Is Not Corrected?

This condition, if not detected and corrected, could result in failure of the steering jack piston rod. Such failure could lead to loss of steering control of the airplane during takeoff, landing, and taxi operations.

Is There Service Information That Applies to This Subject?

British Aerospace has issued Jetstream Mandatory Service Bulletin 32-JA020741, Original issue: November 2, 2002.

What Are the Provisions of This Service Information? This Service Bulletin Specifies:

—Inspecting the steering jack piston rod for cracks and replacing if necessary;

—Measuring the torque setting of the steering jack piston rod end fitting and stop bolt;

—Measuring the thickness of the tab washers; and

—Calculating a new safe life limit for the piston rod.

This service bulletin also references APPH Ltd. Service Bulletin 32-76 (pages 1, 2, and 4 through 7, dated October 2002; and page 3, Erratum 1, dated November 2002), which includes procedures for accomplishing the actions specified in British Aerospace Jetstream Mandatory Service Bulletin 32-JA020741, Original issue: November 2, 2002.

What Action Did the CAA Take?

The CAA classified these service bulletins as mandatory in order to assure the continued airworthiness of these airplanes in the United Kingdom. The CAA classifying a service bulletin as mandatory is the same in the United Kingdom as the FAA issuing an AD in the United States.

Was This in Accordance With the Bilateral Airworthiness Agreement?

These airplane models are manufactured in the United Kingdom and are type certificated for operation in the United States under the provisions of section 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 FAA informed of the situation described above.

The FAA's Determination and an Explanation of the Provisions of This Proposed AD

What Has FAA Decided?

The FAA has examined the findings of the CAA; reviewed all available information, including the service information referenced above; and determined that:

—The unsafe condition referenced in this document exists or could develop on other British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 airplanes of the same type design that are on the U.S. registry;

—The actions specified in the previously-referenced service information should be accomplished on the affected airplanes; and

—AD action should be taken in order to correct this unsafe condition.

What Would This Proposed AD Require?

This proposed AD would require you to inspect the steering jack piston rod for cracks and replace if necessary; measure the torque setting of the steering jack piston rod end fitting and Start Printed Page 3834stop bolt; and measure the thickness of the tab washers. This proposed AD would also require you to calculate a new safe life limit for the steering jack piston rod based on the results of the proposed inspection and the proposed measurements,

Cost Impact

How Many Airplanes Would This Proposed AD Impact?

We estimate that this proposed AD affects 250 airplanes in the U.S. registry.

What Would Be the Cost Impact of This Proposed AD on Owners/Operators of the Affected Airplanes?

We estimate the following costs to accomplish the proposed inspection:

Labor costParts costTotal cost per airplaneTotal Cost on U.S. operators
1 workhour × $60 = $60No parts required$60$60 × 250 = $15,000

We estimate the following costs to accomplish any necessary replacements of the steering jack piston rod that would be required based on the results of the proposed inspection and/or measurements. We have no way of determining the number of airplanes that may need such replacement:

Labor costParts costTotal cost per airplane
8 workhours X $60 = $240$5,300$240 + $5,300 = $5,540

Compliance Time of this Proposed AD

What Would Be the Compliance Time of This Proposed AD?

The compliance time of this proposed AD is “within the next 90 days or 200 ground-air-ground (GAG) cycles after the effective date of this AD, whichever occurs first.”

Why Is the Compliance Time Presented in Calendar Time and Operational Time?

Failure of the steering jack piston rod is only unsafe during airplane operation; this condition is not a result of the number of times the airplane is operated. The cause of the unsafe condition is the result of incorrect torque settings used on the steering jack piston rod end fitting during assembly. We have no way of determining when the unsafe condition occurred on the affected airplanes. For this reason, the FAA has determined that a compliance based on calendar time and operational time should be utilized in this proposed AD in order to assure that the unsafe condition is not allowed to go uncorrected over time.

Regulatory Impact

Would This Proposed AD Impact Various Entities?

The regulations proposed herein would not have a substantial direct effect 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, it is determined that this proposed rule would not have federalism implications under Executive Order 13132.

Would This Proposed AD Involve a Significant Rule or Regulatory Action?

For the reasons discussed above, I certify that this proposed 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) 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 has been placed in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES.

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

The Proposed Amendment

Accordingly, under 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:

Start Part

PART 39—AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Start Authority

Authority: 49 U.S.C. 106(g), 40113, 44701.

End Authority
[Amended]

2. FAA amends § 39.13 by adding a new airworthiness directive (AD) to read as follows:

British Aerospace: Docket No. 2002-CE-56-AD.

(a) What airplanes are affected by this AD? This AD affects Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 airplanes, all serial numbers, that are certificated in any category.

(b) Who must comply with this AD? Anyone who wishes to operate any of the airplanes identified in paragraph (a) of this AD must comply with this AD.

(c) What problem does this AD address? The actions specified by this AD are intended to detect, correct, and prevent cracks in the steering jack piston rod, which could result in failure of the steering jack piston rod. Such failure could lead to loss of steering control of the airplane during takeoff, landing, and taxi operations.

(d) What actions must I accomplish to address this problem? To address this problem, you must accomplish the following:

Start Printed Page 3835
ActionsComplianceProcedures
(1) Insepct the steering jack piston rod for cracks. (i) If cracks are found, replace the cracked steering jack piston rod. Install the new steering jack piston rod using a torque setting of 175 lbf (pound force) inch or 20 Nm (Newton meters) when tightening the end fitting and stop bolt (ii) If no cracks are found, determine the torque setting of the steering jack piston rod end fitting and stop bolt.Inspect within the next 90 days or 200 ground-air-ground (GAG) cycles after the effective date of this AD, whichever occurs first. Replace cracked steering jack piston rods or determine torque settings prior to further flightIn accordance with the procedures in APPH Ltd. Service Bulletin 32-76 (pages 1, 2, and 4 through 7, dated October 2002; and page 3, Erratum 1, dated November 2002), as referenced in Britich Aerospace Jetstream Mandatory Service Bulletin 32-JA020741, Original Issue: November 2, 2002.
(2) If the torque setting of the steering jack piston rod end fitting or stop bolt is greater than 175 lbf inch or 20 Nm and is equal to or les than 435 lbf inch or 49 Nm: (i) Calculate the new safe life limit for the steering jack piston rod; and (ii) Incorporate the following into the Aircraft Logbook: “In accordance with AD**—**—**, the steering jack piston rod is life limited to___.”Prior to further flight after the inspection required in paragraph (d)(1) of this ADIn accordance with the procedures in APPH Ltd. Service Bulletin 32-76, (pages 1, 2, and 4 through 7, dated October 2002; and page 3, Erratum 1, dated November 2002), as referenced in British Aerospace Jetstream Mandatory Service Bulletin 32-JA020741, Original Issue: November 2, 2002.
(3) If the torque setting of the steering jack piston rod end fitting or stop bolt is greater than 435 lbf inch or 49 Nm, measure the deformation thickness of the tab washers  (i) If the tab washer deformation thickness is greater than 0.001 inch and is equal to or less than 0.005 inch, calculate a new safe life limit for the steering jack piston rod, and incorporate the following into the Aircraft Logbook: “In accordance with AD **—**—**—, the steering jack piston rod is life limited to ___.” (ii) If the tab washer deformation thickness is greater than 0.005 inch, replace the steering jack piston rod using the torque settings specified in paragraph (d)(1) of this AD.Prior to further flight after the inspection required in paragraph (d)(1) of this ADIn accordance with the procedures in APPH Ltd. Service Bulletin 32-76, (pages 1, 2, and 4 through 7, dated October 2002; and page 3, Erratum 1, dated November 2002), as referenced in British Aerospace Jetstream Mandatory Service Bulletin 32-JA020741, Original Issue: November 2, 2002.
(4) Do not install any steering jack piston rod unless it has been inspected, determined to be free of cracks, and the safe life limit has been establishedAs of the effective date of this ADIn accordance with the procedures in APPH Ltd. Service Bulletin 32-76, (pages 1, 2, and 4 through 7, dated October 2002; and page 3, Erratum 1, dated November 2002), as referenced in British Aerospace Jetstream Mandatory Service Bulletin 32-JA020741, Original Issue: November 2, 2002.

Note 1:

If the owners/operators of the affected airplanes have not kept track of ground-air-ground (GAG) cycles, hours time-in-service (TIS) may be substituted by calculating 1.5 GAG cycles per hour TIS. For example, 3,000 GAG cycles would equal 2,000 hours TIS.

(e) Can I comply with this AD in any other way? You may use an alternative method of compliance or adjust the compliance time if:

(1) Your alternative method of compliance provides an equivalent level of safety; and

(2) The Standards Office Manager, Small Airplane Directorate, approves your alternative. Submit your request through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Standards Office Manager.

Note 2:

This AD applies to each airplane identified in paragraph (a) of this AD, 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 (e) 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 you have not eliminated the unsafe condition, specific actions you propose to address it.

(f) Where can I get information about any already-approved alternative methods of compliance? Contact Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: (816) 329-4090.

(g) What if I need to fly the airplane to another location to comply with this AD? The FAA can issue a special flight permit under sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a location where you can accomplish the requirements of this AD.

(h) How do I get copies of the documents referenced in this AD? You may get copies of the documents referenced in this AD from British Aerospace Regional Aircraft, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland; telephone: (01292) 672345; facsimile: (01292) 671625. You may view these documents at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.

Note 3:

The subject of this AD is addressed in British Aerospace Jetstream Mandatory Service Bulletin 32-JA020741, Original Issue: November 2, 2002. This service bulletin is classified as mandatory by the United Kingdom Civil Aviation Authority (CAA).

Start Signature
Start Printed Page 3836

Issued in Kansas City, Missouri, on January 15, 2003.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft Certification Service.

End Signature End Part End Supplemental Information

[FR Doc. 03-1677 Filed 1-24-03; 8:45 am]

BILLING CODE 4910-13-P