[Federal Register: January 27, 2003 (Volume 68, Number 17)]
[Proposed Rules]
[Page 3832-3836]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27ja03-25]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-CE-56-AD]
RIN 2120-AA64
Airworthiness Directives; British Aerospace Model HP.137
Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and
Jetstream Model 3201 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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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
[[Page 3833]]
506, 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.
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.
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
[[Page 3834]]
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,
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:
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Total cost
Labor cost Parts cost per Total Cost on U.S. operators
airplane
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1 workhour x $60 = $60............... No parts required...... $60 $60 x 250 = $15,000
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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:
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Labor cost Parts cost Total cost per airplane
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8 workhours X $60 = $240...................... $5,300 $240 + $5,300 = $5,540
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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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
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:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. FAA amends Sec. 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:
[[Page 3835]]
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Actions Compliance Procedures
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(1) Insepct the steering Inspect within the In accordance with
jack piston rod for cracks. next 90 days or 200 the procedures in
(i) If cracks are found, ground-air-ground APPH Ltd. Service
replace the cracked (GAG) cycles after Bulletin 32-76
steering jack piston rod. the effective date (pages 1, 2, and 4
Install the new steering of this AD, through 7, dated
jack piston rod using a whichever occurs October 2002; and
torque setting of 175 lbf first. Replace page 3, Erratum 1,
(pound force) inch or 20 Nm cracked steering dated November
(Newton meters) when jack piston rods or 2002), as
tightening the end fitting determine torque referenced in
and stop bolt. settings prior to Britich Aerospace
(ii) If no cracks are found, further flight. Jetstream Mandatory
determine the torque Service Bulletin 32-
setting of the steering JA020741, Original
jack piston rod end fitting Issue: November 2,
and stop bolt.. 2002.
-----------------------------
(2) If the torque setting of Prior to further In accordance with
the steering jack piston flight after the the procedures in
rod end fitting or stop inspection required APPH Ltd. Service
bolt is greater than 175 in paragraph (d)(1) Bulletin 32-76,
lbf inch or 20 Nm and is of this AD. (pages 1, 2, and 4
equal to or les than 435 through 7, dated
lbf inch or 49 Nm: October 2002; and
(i) Calculate the new safe page 3, Erratum 1,
life limit for the steering dated November
jack piston rod; and 2002), as
(ii) Incorporate the referenced in
following into the Aircraft British Aerospace
Logbook: ``In accordance Jetstream Mandatory
with AD**--**--**, the Service Bulletin 32-
steering jack piston rod is JA020741, Original
life limited to------.'' Issue: November 2,
2002.
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(3) If the torque setting of Prior to further In accordance with
the steering jack piston flight after the the procedures in
rod end fitting or stop inspection required APPH Ltd. Service
bolt is greater than 435 in paragraph (d)(1) Bulletin 32-76,
lbf inch or 49 Nm, measure of this AD. (pages 1, 2, and 4
the deformation thickness through 7, dated
of the tab washers. October 2002; and
(i) If the tab washer page 3, Erratum 1,
deformation thickness is dated November
greater than 0.001 inch and 2002), as
is equal to or less than referenced in
0.005 inch, calculate a new British Aerospace
safe life limit for the Jetstream Mandatory
steering jack piston rod, Service Bulletin 32-
and incorporate the JA020741, Original
following into the Aircraft Issue: November 2,
Logbook: ``In accordance 2002.
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..
-----------------------------
(4) Do not install any As of the effective In accordance with
steering jack piston rod date of this AD. the procedures in
unless it has been APPH Ltd. Service
inspected, determined to be Bulletin 32-76,
free of cracks, and the (pages 1, 2, and 4
safe life limit has been through 7, dated
established. 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.
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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).
[[Page 3836]]
Issued in Kansas City, Missouri, on January 15, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-1677 Filed 1-24-03; 8:45 am]
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