[Federal Register Volume 68, Number 24 (Wednesday, February 5, 2003)]
[Rules and Regulations]
[Pages 5822-5825]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-2784]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-07-AD; Amendment 39-13043; AD 2003-03-18]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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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, re-rig 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 mis-rigged 
elevator control system, which could lead to insufficient elevator 
control authority and loss of control of the airplane.

DATES: The AD becomes effective February 5, 2003, to all affected 
persons who did not receive emergency AD 2003-03-18, issued January 27, 
2003. Emergency AD 2003-03-18 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.

ADDRESSES: Submit comments to FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2003-CE-07-AD, 901 
Locust, Room 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: [email protected]. 
Comments sent electronically must contain ``Docket No. 2003-CE-07-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 view information related to this AD at FAA, Central Region, 
Office of the Regional Counsel, Attention: Rules Docket No. 2003-CE-07-
AD, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the Office 
of the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Paul DeVore, Aerospace Engineer, FAA, 
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, 
Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-
4142; facsimile: (316) 946-4407.

SUPPLEMENTARY INFORMATION:

Discussion

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 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 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 mis-rigged 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 2003-03-18 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, re-rig 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 time-in-service (TIS); and
    --Report the results of the initial inspection and the 100-hour 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.

[[Page 5823]]

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 self-addressed, stamped postcard. On the postcard, 
write ``Comments to Docket No. 2003-CE-07-AD.'' 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 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:

2003-03-18 Raytheon Aircraft Company: Amendment 39-13043; Docket No. 
2003-CE-07-AD.

    (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 mis-rigged 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         03-18. 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
 appropriately-rated           after the
 maintenance person perform    inspection required
 a full pitch-down to full     by paragraph
 pitch-up 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
 pitch-down 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.

[[Page 5824]]

 
(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),           re-rigged. Examples   or 1900D
 (d)(3)(i), and (d)(3)(ii)     of items that         maintenance manual.
 of this AD. If the aft        require re-rigging
 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, push-pull
                               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     67201-0085;
 paragraph (d)(3)(i) of this   AD.                   telephone: (800)
 AD. Break out the results                           429-5372 or (316)
 of the control column sweep                         676-3140;
 inspection, bolt length                             facsimile; (316)
 measurement, and the travel                         676-8051; e-mail:
 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 2003-03-18''.
------------------------------------------------------------------------

    (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 already-approved 
alternative methods of compliance? Contact Paul DeVore, Aerospace 
Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport 
Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; 
telephone: (316) 946-4142; facsimile: (316) 946-4407.
    (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

[[Page 5825]]

of this AD provided the following is adhered to:
    (1) When re-rigging 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 2003-03-18, issued January 27, 2003. Emergency 
AD 2003-03-18 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. 03-2784 Filed 2-4-03; 8:45 am]
BILLING CODE 4910-13-P