Airworthiness Directives; Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes

[Federal Register Volume 67, Number 159 (Friday, August 16, 2002)]
[Rules and Regulations]
[Pages 53467-53469]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-20513]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-159-AD; Amendment 39-12862; AD 2002-16-23]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-600, -700, -700C, -
800, and -900 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Boeing Model 737-600, -700, -700C, -800, and 
``900 series airplanes. This action requires repetitive tests of the 
rudder pedal force or repetitive inspections of the rudder feel and 
centering unit to determine the condition of the inner spring; 
corrective action if necessary; and eventual replacement of the spring 
assembly on the rudder feel and centering unit with a new assembly, 
which would terminate the repetitive requirements. This action is 
necessary to prevent reduced rudder pedal feel and centering force, 
which, combined with failure of the outer spring of the spring 
assembly, could result in pilot-induced oscillation and consequent loss 
of control of the airplane. This action is intended to address the 
identified unsafe condition.

DATES: Effective September 3, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 3, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before October 15, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-159-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected] . Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-159-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in this AD may be obtained from 
Boeing Commercial Airplane Group, PO Box 3707, Seattle, Washington 
98124-2207. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Technical Information : Douglas Tsuji, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, 
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-1506; fax (425) 227-1181.
    Other Information : Sandi Carli, Airworthiness Directive Technical 
Editor/Writer; telephone (425) 687-4243, fax (425) 227-1232. Questions 
or comments may also be sent via the Internet using the following 
address: [email protected]. Questions or comments sent via the 
Internet as attached electronic files must be formatted in Microsoft 
Word 97 for Windows or ASCII text.

SUPPLEMENTARY INFORMATION: The FAA has received reports of low rudder 
pedal forces caused by a broken inner spring in the rudder feel and 
centering unit on some Boeing Model 737-600, -700, -700C, -800, and -
900 series airplanes. The rudder feel and centering unit has two 
springs--an inner spring and an outer spring. Investigation of the 
broken springs revealed an incorrect manufacturing process used on a 
specific batch of inner springs. The outer springs were processed in 
separate lots, and no outer spring failures have been reported. Further 
investigation revealed broken inner springs on three delivered and four 
undelivered airplanes. In each case, the reduced rudder pedal centering 
force was caused by a failed inner spring. A preflight controls check 
conducted by the flight crew will detect reduced pedal force, which 
would indicate the failure of either spring. In the event that both the 
inner and outer springs fail, the pedal feel and centering forces will 
be lost. This condition, if not corrected, could

[[Page 53468]]

result in pilot-induced oscillation and consequent loss of control of 
the airplane.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
737-27A1259, dated May 30, 2002. The alert service bulletin describes 
procedures for repetitive rudder pedal force tests to measure the pedal 
force, and repetitive inspections of the rudder feel and centering unit 
to determine if an inner spring is loose or broken. Operators may 
choose to do either the test or the inspection. The alert service 
bulletin also describes procedures for replacing the spring assembly on 
the rudder feel and centering unit with a new assembly, and adding the 
suffix ``R'' to the serial number to indicate that the spring assembly 
was replaced. Replacing the spring assembly is considered corrective 
action for incorrect pedal force or a loose/broken inner spring, and 
eliminates the need for the repetitive tests/inspections. The alert 
service bulletin also specifies that operators submit replaced spring 
assemblies and identifying information to the manufacturer. 
Accomplishment of the actions specified in the alert service bulletin 
is intended to adequately address the identified unsafe condition.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, this AD is 
being issued to prevent reduced rudder pedal feel and centering force, 
which, combined with failure of the outer spring of the spring 
assembly, could result in pilot-induced oscillation and consequent loss 
of control of the airplane. This AD requires accomplishment of the 
actions specified in the alert service bulletin described previously, 
except as discussed in the following section.
    This AD also requires that operators send replaced spring 
assemblies to Boeing. According to the alert service bulletin, receipt 
of all replaced spring assemblies will ensure that discrepant springs 
have been removed from service. However, since the alert service 
bulletin was issued, Boeing has advised that the replaced spring 
assemblies submitted by operators will be examined for the type and 
level of damage sustained, so that further action based on the findings 
may be developed if appropriate.

Differences Between AD and Alert Service Bulletin

    This AD includes Model 737-600 series airplanes. In the alert 
service bulletin, this model was identified in the Summary 
(``EFFECTIVITY''), but apparently inadvertently omitted in paragraph 
1.A.1.
    In addition, the applicability of this AD includes airplanes having 
line numbers 948 through 1108. The effectivity of the alert service 
bulletin includes those same airplane line numbers--but ``with some 
exceptions.'' Those exceptions include four airplanes that Boeing has 
since advised should be included in the service bulletin effectivity. 
Those four airplanes have line numbers between 948 and 1108 and are 
therefore subject to the requirements of this AD.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Submit comments using the following format:
    <bullet> Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    <bullet> For each issue, state what specific change to the AD is 
being requested.
    <bullet> Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2002-NM-159-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it 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. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to 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:


[[Page 53469]]


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


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-16-23  Boeing: Amendment 39-12862. Docket 2002-NM-159-AD.

    Applicability: Model 737-600, -700, -700C, -800, and -900 series 
airplanes; certificated in any category; line numbers 948 through 
1108 inclusive.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, 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 the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent reduced rudder pedal feel and centering force, which, 
combined with failure of the outer spring of the spring assembly, 
could result in pilot-induced oscillation and consequent loss of 
control of the airplane, accomplish the following:

Test or Inspection

    (a) Within 10 days after the effective date of this AD, do the 
actions specified in either paragraph (a)(1) or (a)(2) of this AD, 
in accordance with Part A of paragraph 3.B. of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-27A1259, dated May 
30, 2002. Repeat either action at least every 20 days until the 
terminating action required by paragraph (b) of this AD has been 
done.
    (1) Test the force of the rudder pedal. If the pedal force is 
outside the limits specified in the alert service bulletin: Before 
further flight, do the terminating action specified by paragraph (b) 
of this AD.
    (2) Perform a detailed inspection of the rudder feel and 
centering unit to determine the condition of the inner spring. If 
the inner spring is loose or broken: Before further flight, do the 
terminating action specified by paragraph (b) of this AD.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

Terminating Action

    (b) Except as required by paragraphs (a)(1) and (a)(2) of this 
AD: Within 90 days after the effective date of this AD, replace the 
spring assembly on the rudder feel and centering unit with a new 
spring assembly, and ensure that the letter ``R'' is marked after 
the serial number; in accordance with Part B of paragraph 3.B. of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-27A1259, dated May 30, 2002.

Reporting Requirement

    (c) At the applicable time specified in paragraph (c)(1) or 
(c)(2) of this AD: Submit the replaced spring assembly P/N 69-57900-
5, if applicable, along with a report that includes identifying 
information to Richard Ranhofer, The Boeing Company, Spares 
Distribution Center, Repair and Overhaul Area SSA111, Building 2201, 
Door W10, 2201 South 142nd Street, SeaTac, Washington 98168; 
reference SB 737-27A1259. The report must include the airplane 
identification (line number, serial number, omni number, or registry 
number), and the serial number of the rudder feel and centering 
unit. This may be accomplished by submitting a completed Appendix B 
of Boeing Alert Service Bulletin 737-27A1259, dated May 30, 2002. 
Information collection requirements contained in this AD have been 
approved by the Office of Management and Budget (OMB) under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et 
seq.) and have been assigned OMB Control Number 2120-0056.
    (1) For airplanes on which the inspection is accomplished after 
the effective date of this AD: Send the spring assembly and the 
report within 30 days after replacing the spring assembly, as 
required by paragraph (a) or (b), as applicable, of this AD.
    (2) For airplanes on which the spring assembly has been replaced 
prior to the effective date of this AD: Send the spring assembly and 
the report within 30 days after the effective date of this AD.

Spare Parts

    (d) As of the effective date of this AD, no person may install 
on any airplane a rudder feel and centering unit with a spring 
assembly that has a part number 69-57900-5 and a serial number in 
the range 2900 through 3101 inclusive--unless the feel and centering 
unit's serial number includes the suffix ``R'' to indicate that the 
spring assembly has been replaced.

Alternative Methods of Compliance

    (e) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Seattle ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits: Prohibited

    (f) Special flight permits, in accordance with Secs. 21.197 and 
21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 
21.199), are prohibited for the operation of the airplane to a 
location where the requirements of this AD can be accomplished.

Incorporation by Reference

    (g) The actions must be done in accordance with Boeing Alert 
Service Bulletin 737-27A1259, dated May 30, 2002. This incorporation 
by reference was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
obtained from Boeing Commercial Airplane Group, PO Box 3707, 
Seattle, Washington 98124-2207. Copies may be inspected at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (h) This amendment becomes effective on September 3, 2002.

    Issued in Renton, Washington, on August 7, 2002.
Vi Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-20513 Filed 8-15-02; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T04:18:40.459129+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

7679cb5e6667712b2f2dea1c1681317b4a84977f55607abac5292af12c6974ce

Text SHA-256

9215c55eb6b9454fcc53f8c5f6a7479a05cda26d56b588c22c1acdcf8e3bb9b2