
[Federal Register Volume 77, Number 29 (Monday, February 13, 2012)]
[Rules and Regulations]
[Pages 7521-7523]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-3115]



[[Page 7521]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0571; Directorate Identifier 2010-NM-263-AD; 
Amendment 39-16950; AD 2012-03-09]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Model 747SP series airplanes. This AD was prompted by a report of a 
rudder hard-over event on a Model 747-400 series airplane, caused by a 
rudder power control module (PCM) manifold cracking and separating in 
the area of the yaw damper cavity end-cap. This condition could result 
in a hard-over of the rudder surface leading to an increase in pilot 
workload and a possible high-speed runway excursion upon landing, in 
the event of failure of the lower or upper rudder PCM manifold. This AD 
requires replacing or modifying the upper and lower rudder PCMs. We are 
issuing this AD to correct the unsafe condition on these products.

DATES: This AD is effective March 19, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of March 19, 
2012.

ADDRESSES: For Boeing 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; email: 
me.boecom@boeing.com; Internet https://www.myboeingfleet.com. For 
Parker service information identified in this AD, contact Parker 
Aerospace, 14300 Alton Parkway, Irvine, California 92618; telephone 
949-833-3000; Internet http://www.parker.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.

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 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Marie Hogestad, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057-
3356; phone: 425-917-6418; fax: 425-917-6590; email: 
marie.hogestad@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on June 22, 2011 (76 FR 
36390). That NPRM proposed to require replacing or modifying the upper 
and lower rudder PCMs.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and the FAA's response to each comment.

Support for the NPRM (76 FR 36390, June 22, 2011)

    The National Transportation Safety Board fully supports the NPRM 
(76 FR 36390, June 22, 2011).

Request To Clarify the Discussion Section and Paragraph (e) of NPRM (76 
FR 36390, June 22, 2011)

    Boeing requested that we revise the Discussion section and 
paragraph (e) of the NPRM (76 FR 36390, June 22, 2011) to clarify that 
the corrective actions are not intended to prevent the manifold from 
cracking, but rather to prevent the cracking of the manifold from 
progressing to a rudder surface hard-over. Boeing pointed out that the 
secondary retention device incorporated in Boeing Alert Service 
Bulletin 747-27A2497, dated September 30, 2010, prevents the yaw damper 
modulating piston assembly from shifting after a manifold failure, 
therefore, preventing a rudder surface hard-over. Boeing suggested 
removing the phrase, ``if not corrected,'' from the sentence, 
``Cracking in a rudder PCM manifold, if not corrected, could result in 
a failure of the upper or lower rudder PCM manifold which could result 
in a hard-over of the rudder surface leading to an increase in pilot 
workload and a possible high-speed runway excursion upon landing.'' In 
addition, Boeing suggested revising the sentence, ``Although commanding 
full retract, pilot pedal inputs were ineffective in moving the lower 
rudder back to the right,'' to replace the term ``retract'' with 
``right rudder,'' and revising the sentence, ``These events did not 
result in a hard-over, but created the need for a retention feature 
solution specified in AD 2008-13-03, Amendment 39-15566, for Model 747-
400, -400D, and -400F series airplanes,'' to clarify that the 
additional three events did not result in end-cap separation or a hard-
over.
    We agree that replacement or modification of the upper and lower 
rudder PCMs is intended to prevent the yaw damper modulating piston 
assembly from shifting after a manifold failure, consequently 
preventing a rudder surface hard-over. Therefore, we have revised 
paragraph (e) and the corresponding language in the Summary of this AD 
to clarify the intent. However, we cannot revise the Discussion section 
of this AD, because that section is not re-stated in this final rule.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (76 FR 36390, June 22, 2011) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (76 FR 36390, June 22, 2011).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 7 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

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                                                 Estimated Costs
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                                                                                                  Cost on U.S.
               Action                      Labor cost          Parts cost     Cost per product      operators
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Replace rudder PCM (P/N 241700-      11 work-hours x $85              $5,856            $6,791           $47,537
 1007).                               per hour = $935.
Replace rudder PCM (P/N 241700-      11 work-hours x $85               8,568             9,503            66,521
 1005).                               per hour = $935.
Modify rudder PCM (P/N 241700-1007)  3 work-hours x $85                1,374             1,629            11,403
                                      per hours = $255.
Modify rudder PCM (P/N 241700-1005)  3 work hours x $85                4,086             4,341            30,387
                                      per hour = $255.
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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

    This AD will not have federalism implications under Executive Order 
13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2012-03-09 The Boeing Company: Amendment 39-16950; Docket No. FAA-
2011-0571; Directorate Identifier 2010-NM-263-AD.

(a) Effective Date

    This AD is effective March 19, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 747SP series 
airplanes, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 27, Flight Controls.

(e) Unsafe Condition

    This AD was prompted by a report of a rudder hard-over event on 
a Model 747-400 series airplane, caused by a rudder power control 
module (PCM) manifold cracking and separating in the area of the yaw 
damper cavity end-cap. We are issuing this AD to prevent a hard-over 
of the rudder surface leading to an increase in pilot workload and a 
possible high-speed runway excursion upon landing, in the event of 
failure of the lower or upper rudder PCM manifold.

(f) Compliance

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

(g) Replace or Modify Rudder PCMs

    Within 24 months or 8,400 flight hours after the effective date 
of this AD, whichever occurs first, do the replacement specified in 
paragraph (g)(1) of this AD or the modification specified in 
paragraph (g)(2) of this AD for the upper and lower rudder PCMs, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-27A2497, dated September 30, 2010.
    (1) Replace any rudder PCM having Boeing part number (P/N) 
60B80093-3 (Parker P/N 241700-1005) or Boeing P/N 60B80093-4 (Parker 
P/N 241700-1007) with rudder PCM having Boeing P/N 60B80093-104 
(Parker P/N 241700-9007).
    (2) Modify any rudder PCM having Boeing P/N 60B80093-3 (Parker 
P/N 241700-1005) or Boeing P/N 60B80093-4 (Parker P/N 241700-1007).

    Note 1 to paragraph (g): Boeing Alert Service Bulletin 747-
27A2497, dated September 30, 2010, refers to Parker Service Bulletin 
241700-27-333, dated January 26, 2010, as an additional source of 
guidance for modifying the upper and lower rudder PCM manifold 
access caps provided in Option 2 of Work Packages 1 and 2 of Boeing 
Alert Service Bulletin 747-27A2497, dated September 30, 2010.

(h) Parts Installation

    As of the effective date of this AD, no person may install a 
rudder PCM having Boeing P/N 60B80093-3 (Parker P/N 241700-1005) or 
Boeing P/N 60B80093-4 (Parker P/N 241700-1007), on any airplane.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(j) Related Information

    For more information about this AD, contact Marie Hogestad, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, 
Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; phone: 425-917-6418; fax: 425-917-6590; 
email: marie.hogestad@faa.gov.

(k) Material Incorporated by Reference

    You must use the following service information to do the actions 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference 
(IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the

[[Page 7523]]

following service information on the date specified:
    (1) Boeing Alert Service Bulletin 747-27A2497, dated September 
30, 2010, approved for IBR March 19, 2012.
    (2) For Boeing 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; email 
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.
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on January 27, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-3115 Filed 2-10-12; 8:45 am]
BILLING CODE 4910-13-P


