Airworthiness Directives; The Boeing Company Model 747SP Series Airplanes, 36390-36392 [2011-15536]

Download as PDF 36390 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; fax (425) 227–1149. Information may be e-mailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. Related Information (k) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2011–0006, dated January 17, 2011; and the service bulletins identified in table 4 of this AD; for related information. TABLE 4—RELATED SERVICE INFORMATION Airbus Mandatory Service Bulletin— Revision— Dated— A300–29–0126 A300–29–0127 A300–29–6063 A300–29–6064 A310–29–2099 A310–29–2100 01 ......................................................................... Original ................................................................ Original ................................................................ Original ................................................................ Original ................................................................ Original ................................................................ October 12, 2010. August 12, 2010. August 12, 2010. August 12, 2010. August 12, 2010. August 12, 2010. ............................................................................................ ............................................................................................ ............................................................................................ ............................................................................................ ............................................................................................ ............................................................................................ Issued in Renton, Washington, on June 10, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–15535 Filed 6–21–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0571; Directorate Identifier 2010–NM–263–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 747SP Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD would require replacing or modifying the upper and lower rudder power control modules (PCM). This proposed AD was prompted by a report of a rudder hard-over event on a Model 747–400 series airplane, caused by a rudder PCM manifold cracking and separating in the area of the yaw damper cavity end-cap. We are proposing this AD to prevent a failure of the lower or upper 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. srobinson on DSK4SPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 19:53 Jun 21, 2011 Jkt 223001 We must receive comments on this proposed AD by August 8, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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. DATES: Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 available in the AD docket shortly after receipt. 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; e-mail: marie.hogestad@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2011–0571; Directorate Identifier 2010– NM–263–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 https:// 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 received a report from an operator of a Model 747–400 series airplane of a lower rudder hard-over event caused by a lower rudder PCM manifold cracking and separating in the area of the yaw damper cavity end-cap. This allowed the yaw damper sleeve to shift, giving the system a lower rudder left input (beyond the yaw damper authority). E:\FR\FM\22JNP1.SGM 22JNP1 36391 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules Yaw damper authority is limited to +/¥ 4 degrees of rudder command. The failure removed the yaw damper end stop and allowed the yaw damper input to exceed the maximum design yaw damper authority. Although commanding full retract, pilot pedal inputs were ineffective in moving the lower rudder back to the right. We also received three additional reports of cracking in the rudder PCM manifold. These events did not result in a hardover, 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. Upon investigation, it was determined that the Model 747SP fleet could be susceptible to the same failure because they use the same manifold sub-assembly as the Model 747–400 series airplanes. 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. Relevant Service Information We reviewed Boeing Alert Service Bulletin 747–27A2497, dated September 30, 2010. The service information describes procedures for either replacing the upper and lower rudder PCMs 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 new rudder PCMs having Boeing P/N 60B80093–104 (Parker P/N 241700–9007); or modifying the upper and lower rudder PCMs having Boeing P/N 60B80093–3 (Parker P/N 241700–1005) or Boeing P/N 60B80093–4 (Parker P/N 241700–1007) by replacing the access cap with a two piece cap that includes a retention feature for the yaw damper modulating piston assembly in the rudder PCM. 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 PCMs provided in Option 2 of Work Packages 1 and 2 of Boeing Alert Service Bulletin 747–27A2497, dated September 30, 2010. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously. Costs of Compliance We estimate that this proposed AD affects 7 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Replace rudder PCM (P/N 241700–1007) ......... Replace rudder PCM (P/N 241700–1005) ......... Modify rudder PCM (P/N 241700–1007) ............ Modify rudder PCM (P/N 241700–1005) ............ 11 work-hours × $85 per hour = $935 ............... 11 work-hours × $85 per hour = $935 ............... 3 work-hours × $85 per hour = $255 ................. 3 work hours × $85 per hour = $255 ................. srobinson on DSK4SPTVN1PROD with PROPOSALS 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 VerDate Mar<15>2010 19:53 Jun 21, 2011 Jkt 223001 Parts cost Cost per product $5,856 8,568 1,374 4,086 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 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), (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. § 39.13 List of Subjects in 14 CFR Part 39 Cost on U.S. operators $6,791 9,503 1,629 4,341 $47,537 66,521 11,403 30,387 Affected ADs Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 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. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA– 2011–0571; Directorate Identifier 2010– NM–263–AD. Comments Due Date (a) We must receive comments by August 8, 2011. (b) None. Applicability (c) This AD applies to all The Boeing Company Model 747SP series airplanes, certificated in any category. E:\FR\FM\22JNP1.SGM 22JNP1 36392 Federal Register / Vol. 76, No. 120 / Wednesday, June 22, 2011 / Proposed Rules Subject (d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 27, Flight Controls. Unsafe Condition (e) 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 failure of the lower or upper rudder PCM manifold, which could result in a hardover of the rudder surface leading to an increase in pilot workload and a possible high-speed runway excursion upon landing. Compliance (f) Comply with this AD within the compliance times specified, unless already done. Replace or Modify Rudder PCMs (g) 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 the 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: 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. srobinson on DSK4SPTVN1PROD with PROPOSALS Parts Installation (h) 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. Alternative Methods of Compliance (AMOCs) (i)(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 e-mailed to: 9–ANM– Seattle–ACO–AMOC–Requests@faa.gov. VerDate Mar<15>2010 19:53 Jun 21, 2011 Jkt 223001 (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. Related Information (j) 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; telephone: 425–917–6418; fax: 425–917–6590; e-mail: marie.hogestad@faa.gov. (k) 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. Issued in Renton, Washington on June 14, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–15536 Filed 6–21–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0572; Directorate Identifier 2011–NM–009–AD] RIN 2120–AA64 Airworthiness Directives; Gulfstream Aerospace Corporation Model GV and GV–SP Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD would require inspecting to determine whether a third Halon fire extinguisher bottle is installed in the auxiliary power unit (APU) fragment impact zone, revising the limitations section of the airplane flight manual to add restrictions for APU usage for certain airplanes having a third fire extinguisher bottle, and removing the third fire extinguisher bottle from certain airplanes. This proposed AD was prompted by notification from the SUMMARY: PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 airplane manufacturer that the third fire extinguisher bottle is mounted in a small-fragment impact zone. We are proposing this AD to prevent penetration of the bottle by fragments released due to a failure of the APU rotor system. The bottle could rupture and cause substantial damage to primary airframe structure and primary flight controls. DATES: We must receive comments on this proposed AD by August 8, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, Georgia 31402–2206; telephone 800–810–4853; fax 912–965– 3520; e-mail pubs@gulfstream.com; Internet https://www.gulfstream.com/ product_support/technical_pubs/pubs/ index.htm. 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 https:// 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanford Proveaux, Aerospace Engineer, Continued Operational Safety and Certificate Management Branch, ACE– 102A, FAA, Atlanta Aircraft Certification Office (ACO) 1701 Columbia Avenue, College Park, Georgia 30337; phone: 404–474–5566; fax: 404– 474–5606; e-mail: sanford.proveaux@faa.gov. E:\FR\FM\22JNP1.SGM 22JNP1

Agencies

[Federal Register Volume 76, Number 120 (Wednesday, June 22, 2011)]
[Proposed Rules]
[Pages 36390-36392]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-15536]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0571; Directorate Identifier 2010-NM-263-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 747SP Series 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD would require replacing or 
modifying the upper and lower rudder power control modules (PCM). This 
proposed AD was prompted by a report of a rudder hard-over event on a 
Model 747-400 series airplane, caused by a rudder PCM manifold cracking 
and separating in the area of the yaw damper cavity end-cap. We are 
proposing this AD to prevent a failure of the lower or upper 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.

DATES: We must receive comments on this proposed AD by August 8, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

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; e-mail: 
marie.hogestad@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2011-0571; 
Directorate Identifier 2010-NM-263-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 https://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 received a report from an operator of a Model 747-400 series 
airplane of a lower rudder hard-over event caused by a lower rudder PCM 
manifold cracking and separating in the area of the yaw damper cavity 
end-cap. This allowed the yaw damper sleeve to shift, giving the system 
a lower rudder left input (beyond the yaw damper authority).

[[Page 36391]]

Yaw damper authority is limited to +/- 4 degrees of rudder command. The 
failure removed the yaw damper end stop and allowed the yaw damper 
input to exceed the maximum design yaw damper authority. Although 
commanding full retract, pilot pedal inputs were ineffective in moving 
the lower rudder back to the right. We also received three additional 
reports of cracking in the rudder PCM manifold. 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. Upon investigation, it was 
determined that the Model 747SP fleet could be susceptible to the same 
failure because they use the same manifold sub-assembly as the Model 
747-400 series airplanes. 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.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-27A2497, dated 
September 30, 2010. The service information describes procedures for 
either replacing the upper and lower rudder PCMs 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 new rudder PCMs having Boeing 
P/N 60B80093-104 (Parker P/N 241700-9007); or modifying the upper and 
lower rudder PCMs having Boeing P/N 60B80093-3 (Parker P/N 241700-1005) 
or Boeing P/N 60B80093-4 (Parker P/N 241700-1007) by replacing the 
access cap with a two piece cap that includes a retention feature for 
the yaw damper modulating piston assembly in the rudder PCM.
    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 PCMs provided in Option 2 of Work Packages 1 and 2 of 
Boeing Alert Service Bulletin 747-27A2497, dated September 30, 2010.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type designs.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously.

Costs of Compliance

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

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

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 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),
    (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.

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 
airworthiness directive (AD):

The Boeing Company: Docket No. FAA-2011-0571; Directorate Identifier 
2010-NM-263-AD.

Comments Due Date

    (a) We must receive comments by August 8, 2011.

Affected ADs

    (b) None.

Applicability

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

[[Page 36392]]

Subject

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

Unsafe Condition

    (e) 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 failure 
of the lower or upper 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.

Compliance

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

Replace or Modify Rudder PCMs

    (g) 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 the 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:  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.

Parts Installation

    (h) 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.

Alternative Methods of Compliance (AMOCs)

    (i)(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 e-mailed 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.

Related Information

    (j) 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; telephone: 425-917-6418; fax: 425-
917-6590; e-mail: marie.hogestad@faa.gov.
    (k) 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.

    Issued in Renton, Washington on June 14, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-15536 Filed 6-21-11; 8:45 am]
BILLING CODE 4910-13-P
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