Document ID: FAA-2009-0212-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Boeing Model 737-600, -700, -700C, -800, -900 and -900ER Series Airplanes
Posted Date: 2009-03-10T04:00Z

[Federal Register: March 10, 2009 (Volume 74, Number 45)]
[Proposed Rules]               
[Page 10197-10199]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10mr09-17]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0212; Directorate Identifier 2008-NM-122-AD]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Boeing Model 737-600, -700, -700C, -800, -900 and -900ER series 
airplanes. This proposed AD would require repetitive testing of the 
rudder pedal forces or repetitive detailed inspections of the inner 
spring of the rudder feel and centering unit, and corrective actions if 
necessary. This proposed AD also requires replacement of the spring 
assembly in the rudder feel and centering unit, which terminates the 
repetitive tests or inspections. This proposed AD results from reports 
of low rudder pedal forces that were caused by a broken inner spring in 
the rudder feel and centering unit; a broken inner spring in 
conjunction with a broken outer spring would significantly reduce 
rudder pedal forces. We are proposing this AD to prevent reduced rudder 
pedal forces, which could result in increased potential for pilot-
induced oscillations and reduce the ability of the flightcrew to 
maintain the safe flight and landing of the airplane.

DATES: We must receive comments on this proposed AD by April 24, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, 
extension 1, fax 206-766-5680; e-mail me.boecom@boeing.com; Internet 
https://www.myboeingfleet.com. You may review copies of the referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221 or 425-227-
1152.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility 
between 9

[[Page 10198]]

a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this proposed AD, the regulatory evaluation, any 
comments received, and other information. The street address for the 
Docket Office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Kelly McGuckin, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6490; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0212; 
Directorate Identifier 2008-NM-122-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received reports of low rudder pedal forces that were 
caused by a broken inner spring in the rudder feel and centering unit; 
a broken inner spring in conjunction with a broken outer spring would 
significantly reduce rudder pedal forces. Investigation of the removed 
parts revealed the root cause of the spring failure to be a material 
defect within the raw material of the wire stock. Boeing determined 
which rudder feel and centering units could be affected based on one 
batch of raw material, and then determined which airplanes have 
discrepant springs installed. This condition, if not corrected, could 
result in reduced rudder pedal forces, which could result in increased 
potential for pilot-induced oscillations and reduce the ability of the 
flightcrew to maintain the safe flight and landing of the airplane.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 737-27A1287, dated 
April 16, 2008. The service bulletin describes procedures for 
repetitive testing of the rudder pedal forces or detailed repetitive 
inspections of the inner spring of the rudder feel and centering unit, 
and corrective actions if necessary. The corrective actions include the 
following: If the rudder pedal force measured during the test is less 
than 60 pounds, the service bulletin describes procedures for replacing 
the spring assembly. If the rudder pedal force measured is higher than 
82.0 pounds, the service bulletin describes procedures for an 
adjustment to rudder control cables RA and RB and performing the rudder 
pedal forces test again. If an inner spring is found loose or there is 
an indication of failure during the detailed inspection, the service 
bulletin describes procedures for replacing the spring assembly.
    The service bulletin also describes procedures for eventual 
replacement of the spring assembly in the rudder feel and centering 
unit and marking the letter `R' after the serial number to indicate the 
replacement was done. The replacement would eliminate the need for the 
repetitive tests or inspections.

FAA's Determination and Requirements of this Proposed AD

    We are issuing this AD because we evaluated all relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design. 
This proposed AD would require accomplishing the actions specified in 
the service information described previously, except as discussed under 
``Difference Between the Proposed AD and Service Information.''

Difference Between the Proposed AD and Service Information

    The airplanes identified in the effectivity section of the service 
bulletin are airplanes on which the discrepant springs were installed, 
and on which the inspection or testing and replacement would be 
required. However, the applicability in this proposed AD includes all 
Boeing Model 737-600, -700, -700C, -800, -900, and -900ER series 
airplanes because of the proposed requirement prohibiting future 
installation of the discrepant springs on those airplanes.

Costs of Compliance

    We estimate that this proposed AD would affect 70 airplanes of U.S. 
registry. The following table provides the estimated costs for U.S. 
operators to comply with this proposed AD.

                                                                 Table--Estimated costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                          Number of U.S.-
                  Action                      Work hours     Average labor       Parts            Cost per product          registered      Fleet cost
                                                             rate per hour                                                   airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Test or Inspection........................               1             $80              $0  $80, per test or inspection               70          $5,600
                                                                                             cycle.
Replacement...............................               3              80           3,138  $3,378......................              70         236,460
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the

[[Page 10199]]

distribution of power and responsibilities among the various levels of 
government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866,
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979), and
    3. 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The FAA amends Sec.  39.13 by adding the following new AD:

Boeing: Docket No. FAA-2009-0212; Directorate Identifier 2008-NM-
122-AD.

Comments Due Date

    (a) We must receive comments by April 24, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Boeing Model 737-600, -700, -700C, -
800, -900 and -900ER series airplanes, certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 27: Flight 
controls.

Unsafe Condition

    (e) This AD results from reports of low rudder pedal forces that 
were caused by a broken inner spring in the rudder feel and 
centering unit; a broken inner spring in conjunction with a broken 
outer spring would significantly reduce rudder pedal forces. We are 
issuing this AD to prevent reduced rudder pedal forces, which could 
result in increased potential for pilot-induced oscillations and 
reduce the ability of the flightcrew to maintain the safe flight and 
landing of the airplane.

Compliance

    (f) Comply with this AD within the compliance times specified, 
unless already done.

Test/Inspection

    (g) For Model 737-600, -700, -700C, -800, and -900 series 
airplanes identified in Boeing Alert Service Bulletin 737-27A1287, 
dated April 16, 2008: Within 30 days after the effective date of 
this AD, perform a test of the rudder pedal forces or a detailed 
inspection of the inner spring of the rudder feel and centering 
unit, by doing all the applicable actions, including all applicable 
corrective actions before further flight, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
27A1287, dated April 16, 2008. Repeat the test or inspection 
thereafter at intervals not to exceed 120 days.

Terminating Action

    (h) For Model 737-600, -700, -700C, -800, and -900 series 
airplanes identified in Boeing Alert Service Bulletin 737-27A1287, 
dated April 16, 2008: Within 36 months after the effective date of 
this AD, replace the spring assembly in the rudder feel and 
centering unit in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 737-27A1287, dated April 16, 2008. 
Accomplishing the replacement ends the repetitive tests or 
inspections required by paragraph (g) of this AD.

Parts Installation

    (i) For all airplanes: As of the effective date of this AD, no 
person may install, on any airplane, a rudder feel and centering 
unit having part number (P/N) 65C25410-7, serial numbers 3609 
through 3820 inclusive, unless it has been modified according to 
paragraph (h) of this AD.

No Reporting Required

    (j) Boeing Alert Service Bulletin 737-27A1287, dated April 16, 
2008, specifies sending a data reporting sheet to Boeing; however, 
this AD does not require that action.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, ATTN: Kelly McGuckin, Aerospace Engineer, Systems and Equipment 
Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601 
Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6490; fax (425) 917-6590; has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, in the FAA 
Flight Standards District Office (FSDO), or lacking a principal 
inspector, your local FSDO. The AMOC approval letter must 
specifically reference this AD.

    Issued in Renton, Washington, on February 27, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E9-5015 Filed 3-9-09; 8:45 am]

BILLING CODE 4910-13-P