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CFR Citation: 14 CFR Part 39

Docket ID: [Docket No. 2003-CE-07-AD; Amendment 39-13043; AD 2003-03-18]

RIN ID: RIN 2120-AA64

NOTICE: RULES

ACTION: Airworthiness directives:

DOCUMENT ACTION: Final rule; request for comments.

SUBJECT CATEGORY: Airworthiness Directives; Raytheon Aircraft Company Beech Models 1900, 1900C, and 1900D Airplanes

DATES: The AD becomes effective February 5, 2003, to all affected persons who did not receive emergency AD 20030318, issued January 27, 2003. Emergency AD 20030318 contained the requirements of this amendment and became effective immediately upon receipt and required the actions 4 days after issuance (January 31, 2003).

The Federal Aviation Administration (FAA) must receive any comments on this rule on or before March 7, 2003.

DOCUMENT SUMMARY: This amendment adopts a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C, and 1900D airplanes. This AD requires you to perform control column sweep and stop bolt inspections to verify full elevator travel to the primary up and down stops and that the stop bolt length is not excessive, rerig the elevator control system if the airplane does not pass the control column sweep and stop inspections, and do a more detailed inspection at a later time if the airplane does pass the inspection. This AD also requires you to report the results of certain inspections. This AD is the result of recent ground testing and a review of the rigging procedures of a Raytheon Beech Model 1900D airplane, which reveals that the elevator control system could be mis rigged to restrict elevator travel if current maintenance procedures are not properly followed. In these instances, it may appear to the crew that they have full elevator control column movement. However, the elevator may not have full travel. Such restricted travel may remain undetected until the airplane is operated in a loading condition that requires full elevator authority to control the pitch. The actions specified by this AD are intended to detect and correct any misrigged elevator control system, which could lead to insufficient elevator control authority and loss of control of the airplane.

SUMMARY: Raytheon,

SUPPLEMENTAL INFORMATION

What Has Happened so Far?

Recent ground testing and a review of the rigging procedures of a Raytheon Beech Model 1900D airplane reveals that the elevator control system could be misrigged to restrict elevator travel if current maintenance procedures are not properly followed. In these instances, it may appear to the crew that they have full elevator control column movement. However, the elevator may not have full travel. Such restricted travel may remain undetected until the airplane is operated in a loading condition that requires full elevator authority to control the pitch.

The Raytheon Beech Models 1900 and 1900C airplanes incorporate the same elevator control system design and are affected by this condition.

In certain loading conditions, a misrigged elevator control system, if not detected and corrected, could lead to insufficient elevator control authority and loss of control of the airplane.

Raytheon has not issued service information regarding this subject. Rigging procedures are included in the applicable Raytheon 1900/1900C or 1900D maintenance manual.

On January 27, 2003, FAA issued emergency AD 20030318 to require you to:

Perform control column sweep and stop bolt inspections to verify full elevator travel to the primary up and down stops and to verify that the stop bolt length is not excessive;

If the airplane does not pass the initial control column sweep and stop bolt inspections, rerig and/or do a more detailed inspection of the elevator control system;

If the airplane does pass the initial control column sweep and stop bolt length inspections, do a more detailed inspection within 100 hours timeinservice (TIS); and

Report the results of the initial inspection and the 100hour TIS inspection (if applicable).

Why Is it Important to Publish This AD?

The FAA found that immediate corrective action was required, that notice and opportunity for prior public comment were impracticable and contrary to the public interest, and that good cause existed to make the AD effective immediately by individual letters issued on January 27, 2003, to all known U.S. operators of Raytheon Beech Models 1900, 1900C, and 1900D airplanes. These conditions still exist, and the AD is published in the Federal Register as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it effective to all persons.
Comments Invited

How Do I Comment on This AD?

Although this action is in the form of a final rule and was not preceded by notice and opportunity for public comment, FAA invites your comments on the 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 specified above.
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We may amend this rule in light of comments received. Factual information that supports your ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether we need to take additional rulemaking action. Are There any Specific Portions of the AD I Should pay Attention to?

We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. You may view all comments we receive before and after the closing date of the rule in the Rules Docket. We will file a report in the Rules Docket that summarizes each FAA contact with the public that concerns the substantive parts of this AD. How Can I Be Sure FAA Receives my Comment?

If you want us to acknowledge the receipt of your written comments, you must include a selfaddressed, stamped postcard. On the postcard, write ``Comments to Docket No. 2003CE07AD.'' We will date stamp and mail the postcard back to you.
Regulatory Impact

Does This AD Impact Various Entities?

These regulations will 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, FAA has determined that this final rule does not have federalism implications under Executive Order 13132.
Does This AD Involve a Significant Rule or Regulatory Action?

We have determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and is not a significant regulatory action under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket (otherwise, an evaluation is not required). A copy of it, if filed, may be obtained from the Rules Docket.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39AIRWORTHINESS 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:
20030318 Raytheon Aircraft Company: Amendment 3913043; Docket No. 2003CE07AD.
(a) What airplanes are affected by this AD? This AD applies to Beech Models 1900, 1900C, and 1900D airplanes, all serial numbers, that are certificated in any category.
(b) Who must comply with this AD? Anyone who operates 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 and correct any misrigged elevator control system, which could lead to insufficient elevator control authority and loss of control of the airplane.
(d) What must I do to address this problem? To address this problem, you must accomplish the following actions:
Actions Compliance Procedures (1) Perform a control column Initially inspect In accordance with sweep inspection to verify within 4 days after the applicable full elevator travel to the February 5, 2003 Raytheon Aircraft primary up and down stops. (the effective date Company 1900/1900C Accomplish this inspection of this AD), except or 1900D using the following that this action maintenance manual. procedures: was required no
(i) Remove the aft fairing later than January
from the vertical 31, 2003, for those
stabilizer to gain visual who received
access to surface stop emergency AD 2003
bolts on the elevator 0318. If
control horn support using necessary,
the applicable Raytheon accomplish the
Aircraft Company 1900/1900C travel board
or 1900D maintenance manual. inspection prior to
(ii) Have another further flight
appropriatelyrated after the
maintenance person perform inspection required
a full pitchdown to full by paragraph
pitchup control column (d)(1)(iii)(B) of
sweep. Visually ensure that this AC.
the elevator control horns
contact the surface stop
bolts for both the full
pitchdown and full pitch
up control column positions.
(iii) Measure the length of
both elevator down stop
bolts from the crown of the
bolt head to the face of
the elevator lower stop
bolt support.
(A) If the dimension of each
stop bolt is equal to or
less than 1.00 inch, the
bolts are acceptable for
the purposes of this
inspection.
(B) If the dimension of
either stop bolt is greater
than 1.00 inch, accomplish
(prior to further flight)
the travel board inspection
procedures as specified in
paragraph (d)(3)(i) of this
AD. If it passes the
procedure specified in
paragraph (d)(3)(i), the
bolt is acceptable even
though it exceeds 1.00 inch.
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(2) If the airplane does not Prior to further In accordance with pass the control column flight after the the applicable sweep inspection or bolt applicable Raytheon Aircraft length requirements of inspection required Company 1900/1900C paragraphs (d)(1)(ii), by paragraphs or 1900D (d)(1)(iii), or (d)(3)(i) (d)(1), (d)(3), and maintenance manual. of this AD. (d)(4) of this AD.
(i) Accomplish the elevator
control system rigging
procedure in accordance
with the applicable
Raytheon Aircraft Company
1900/1900C or 1900D
maintenance manual. Do not
reinstall the aft fairing
because access to the
surface stop bolts is still
necessary;.
(ii) Perform a control
column sweep inspection by
accomplishing the actions
in paragraphs (d)(1)(ii),
(d)(3)(i), and (d)(3)(ii)
of this AD. These actions
are also referenced in
paragraph (d)(4) of this
AD; and.
(iii) When the airplane
passes the requirements of
the above inspection,
replace the aft fairing.
(3) If the airplane passes Replace the aft In accordance with the inspection of paragraph fairing prior to the applicable (d)(1) of this AD, replace further flight Raytheon Aircraft (prior to further flight) after the Company 1900/1900C the aft fairing; and applicable or 1900D accomplish (d)(3)(i) of inspection required maintenance manual. this AD within 100 hours by paragraphs
TIS and any necessary (d)(1), (d)(3), and
actions prior to further (d)(4) of this AD.
flight after that as Unless accomplished
specified in paragraphs per paragraph
(d)(3)(ii) of this AD: (d)(1)(iii)(B) of
(i) Utilizing elevator this AD, accomplish
travel boards, inspect to the travel board
ensure that the surface inspection within
stops on the control horn 100 hours TIS after
support allow the the initial
following:. inspection required
(A) Up elevator travel of 20 by paragraph (d)(1)
degrees, +1 degree 0 of this AD.
degree; and. Accomplish any
(B) Down elevator travel of necessary re
14 degrees, +1 degree 0 rigging prior to
degree. further flight
(ii) If the airplane does after the
not pass the inspection inspection required
required by paragraph by this AD.
(d)(3)(i) of this AD,
accomplish (prior to
further flight) the
elevator control system
rigging procedures as
specified in paragraphs
(d)(2)(i), (d)(2)(ii), and
(d)(3)(i) of this AD.
(4) Perform a control column Prior to further In accordance with sweep inspection by flight after each the applicable accomplishing the actions time the elevator Raytheon Aircraft of paragraphs (d)(1)(i), control system is Company 1900/1900C (d)(1)(ii), (d)(2), rerigged. Examples or 1900D (d)(3)(i), and (d)(3)(ii) of items that maintenance manual. of this AD. If the aft require rerigging
fairing is already removed, include, but are
the actions of paragraphs not limited to,
(d)(1)(i) are not required. changing the
tension on the
elevator primary
control cables and
replacing the
elevator control
system components
such as cables,
pulleys, pushpull
tubes, and
bellcranks.
(5) Report the results of Within 10 days after Submit the results the initial inspection the initial to the Raytheon required by paragraph inspections Aircraft Company, (d)(1) of this AD and the required by 9709 E. Central, initial travel board paragraph (d)(1) or Wichita Kansas inspection required by (d)(3)(i) of this 672010085; paragraph (d)(3)(i) of this AD. telephone: (800) AD. Break out the results 4295372 or (316) of the control column sweep 6763140; inspection, bolt length facsimile; (316) measurement, and the travel 6768051; email: board inspection. Along tom_peay@raytheon. with the results, include com.
the airplane model, serial
number, and the number of
hours TIS at the time of
inspection. Label the
document ``Inspection
results of AD 20030318''.
(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 Manager, Wichita ACO, approves your alternative. Submit your request through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO.

Note: 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 alreadyapproved alternative methods of compliance? Contact Paul DeVore, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209; telephone: (316) 9464142; facsimile: (316) 9464407.
(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
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of this AD provided the following is adhered to:
(1) When rerigging is required, operate the airplane with crew only and no cargo.
(2) All special flight permits must be coordinated with the Wichita ACO at the address, phone number, and facsimile number specified in paragraph (f) of this AD.
(h) Where can I view information related to this AD? You may view information related to this AD at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106.
(i) When does this AD become effective? This AD becomes effective February 5, 2003, to all affected persons who did not receive emergency AD 20030318, issued January 27, 2003. Emergency AD 20030318 contained the requirements of this amendment and became effective immediately upon receipt and required the actions no later than January 31, 2003 (4 days after distribution).

Issued in Kansas City, Missouri, on January 30, 2003. Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 032784 Filed 2403; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Paul DeVore, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209; telephone: (316) 946 4142; facsimile: (316) 9464407.