Airworthiness Directives; The Boeing Company Airplanes, 37781-37783 [2012-14544]

Download as PDF Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations under the criteria of the Regulatory Flexibility Act. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ different part-numbered GCUs on the same helicopter is not approved. DEPARTMENT OF TRANSPORTATION (f) Alternative Methods of Compliance (AMOCs) Federal Aviation Administration (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Mark Wiley, Aerospace Engineer, FAA, Regulations and Policy Group, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5134; fax (817) 222– 5961; email mark.wiley@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2009–0042, dated February 25, 2009. (h) Subject 2012–12–10 Agusta S.p.A. Helicopters: Amendment 39–17090; Docket No. FAA–2012–0013; Directorate Identifier 2010–SW–043–AD. Joint Aircraft Service Component (JASC) Code: 2430, DC generating system. (a) Applicability This AD applies to Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters, with a generator control unit (GCU), part-number (P/N) 1152550–3 installed; certificated in any category. (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on July 10, 2012. (i) Agusta Bollettino Tecnico No. 139–133, Rev. A, dated March 17, 2009. (4) For service information identified in this AD, contact Agusta Westland, Customer Support & Services, Via Per Tornavento 15, 21019 Somma Lombardo (VA) Italy, Attn: Giovanni Cecchelli; telephone 39–0331– 711133; fax 39 0331 711180; or at http:// www.agustawestland.com/technicalbullettins. (5) You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137 or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741– 6030, or go to: http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. (b) Unsafe Condition This AD defines the unsafe condition as a potential fault in the overvoltage protection in GCUs currently installed on Model AB139 and AW139 helicopters. This condition could result in failure of the overvoltage protection of the GCU, degraded performance of the electrical power generation and distribution systems, or fire, and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective July 30, 2012. erowe on DSK2VPTVN1PROD with RULES (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) Remove the No. 1 and No. 2 GCU, P/N 1152550–3. Do not install GCU, P/N 1152550–3, on any helicopter. (2) Modify the electrical connector A13P1 (GCU No. 1) and A14P1 (GCU No. 2) by installing the wiring to the power distribution panel (PDP) for your serialnumbered helicopter as depicted in Figure 1 of Agusta Bollettino Tecnico No. 139–133, Rev. A, dated March 17, 2009. (3) Using either GCU P/N 1152550–4 or GCU P/N 1152550–5, install a No. 1 and No. 2 GCU that has the same part number. Having VerDate Mar<15>2010 14:43 Jun 22, 2012 Jkt 226001 37781 (i) Material Incorporated by Reference Issued in Fort Worth, Texas, on June 8, 2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2012–14797 Filed 6–22–12; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 14 CFR Part 39 [Docket No. FAA–2011–1412; Directorate Identifier 2011–NM–158–AD; Amendment 39–17088; AD 2012–12–08] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777–200 and –300 series airplanes. This AD was prompted by reports of cracked retract actuator fuse pins that can fail earlier than the previously determined safe life limit of the pins. A fractured retract actuator fuse pin can cause the main landing gear to extend without restriction and attempt to lock into position under high dynamic loads. This AD requires an inspection for the part number of the fuse pin, and replacement of the pin if necessary. We are issuing this AD to prevent structural damage to the side and drag brace lock assemblies, which could result in landing gear collapse during touchdown, rollout, or taxi. DATES: This AD is effective July 30, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of July 30, 2012. ADDRESSES: 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; 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. SUMMARY: 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 E:\FR\FM\25JNR1.SGM 25JNR1 37782 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 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: James Sutherland, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6533; fax: 425–917–6590; email: james.sutherland@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 published in the Federal Register on December 30, 2011 (76 FR 82210). That NPRM proposed to require an inspection for the part number of the fuse pin, and replacement of the pin if necessary. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal (76 FR 82210, December 30, 2011) and the FAA’s response to each comment. Request To Revise the Compliance Time and Include Revised Service Information Boeing and United Airlines requested that we revise the NPRM (76 FR 82210, December 30, 2011) to refer to Boeing Special Attention Service Bulletin 777– 32–0083, Revision 2 (not yet released). Boeing stated that it had performed a new risk-based assessment and found that 18 months is adequate to mitigate the remaining fleet risk. Boeing requested the compliance time be changed to 18 months from the date of the service bulletin. Also, Boeing requested that we provide credit for actions accomplished in accordance with Boeing Special Attention Service Bulletin 777–32–0083, Revision 1, dated February 17, 2011. We partially agree. We agree to update the compliance time to 18 months based on the new risk-based safety assessment. We revised paragraphs (g), (g)(2), and (g)(3) of this AD to reflect an initial compliance time of 18 months. We disagree with delaying issuance of the final rule to reference Boeing Special Attention Service Bulletin 777–32– 0083, Revision 2, because that service information is not published at this time. Operators may request approval of an alternative method of compliance (AMOC) once Revision 2 of Boeing Special Attention Service Bulletin 777– 32–0083 is released. 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 82210, December 30, 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 82210, December 30, 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 proposed AD affects 35 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspection ............................................................ 4 work-hours × $85 per hour = $340 ................. $0 $340 $11,900 We estimate the following costs to do any necessary pin replacements that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Pin replacement ....................................... 1 work-hour × $85 per hour = $85 per pin. $769 per pin ............................................ $854 per pin. erowe on DSK2VPTVN1PROD with RULES 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 VerDate Mar<15>2010 14:43 Jun 22, 2012 Jkt 226001 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 PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 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 the DOT Regulatory Policies and E:\FR\FM\25JNR1.SGM 25JNR1 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2012–12–08 The Boeing Company: Amendment 39–17088; Docket No. FAA–2011–1412; Directorate Identifier 2011–NM–158–AD. (a) Effective Date This AD is effective July 30, 2012. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 777–200 and –S300 series airplanes; certificated in any category; as identified in Boeing Special Attention Service Bulletin 777–32–0083, Revision 1, dated February 17, 2011. erowe on DSK2VPTVN1PROD with RULES (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 32: Main landing gear. (e) Unsafe Condition This AD was prompted by reports of cracked retract actuator fuse pins that can fail earlier than the previously determined safe life limit of the pins. A fractured retract actuator fuse pin can cause the main landing gear (MLG) to extend without restriction and attempt to lock into position under high dynamic loads. We are issuing this AD to prevent structural damage to the side and drag brace lock assemblies, which could result in landing gear collapse during touchdown, rollout, or taxi. (f) Compliance Comply with this AD within the compliance times specified, unless already done. VerDate Mar<15>2010 14:43 Jun 22, 2012 Jkt 226001 (g) Inspection of Retract Actuator Fuse Pin Within 18 months after the effective date of this AD: Inspect the part number of the fuse pins of the left and right MLG retract actuators, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–32– 0083, Revision 1, dated February 17, 2011. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the installed actuator fuse pin can be conclusively determined from that review. (1) If any retract actuator fuse pin having part number 112W1769–3 is found installed, no further action is required by this paragraph for that fuse pin. (2) If any retract actuator fuse pin having part number 112W1769–1 is found installed and the pin has accumulated more than 10,000 total flight cycles as of the effective date of this AD: Within 18 months after the effective date of this AD, replace the fuse pin with a new part number 112W1769–3 fuse pin, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–32–0083, Revision 1, dated February 17, 2011. (3) If any retract actuator fuse pin having part number 112W1769–1 is found installed and the pin has accumulated 8,000 or more total flight cycles, but fewer than or equal to 10,000 total flight cycles, as of the effective date of this AD: Before the accumulation of 10,000 total flight cycles on the pin, or within 18 months after the effective date of this AD, whichever occurs later, replace the fuse pin with a new part number 112W1769– 3 fuse pin, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–32– 0083, Revision 1, dated February 17, 2011. (4) If any retract actuator fuse pin having part number 112W1769–1 is found installed and the pin has accumulated fewer than 8,000 total flight cycles as of the effective date of this AD: Before the accumulation of 8,000 total flight cycles on the pin, or within 24 months after the effective date of this AD, whichever occurs later, replace the fuse pin with a new part number 112W1769–3 fuse pin, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777–32–0083, Revision 1, dated February 17, 2011. (h) Parts Installation As of the effective date of this AD, no person may install a retract actuator fuse pin having part number 112W1769–1 on any airplane. (i) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 777–32–0083, dated February 5, 2009. (j) 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 PO 00000 Frm 00033 Fmt 4700 Sfmt 9990 37783 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-ANMSeattle-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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (k) Related Information For more information about this AD, contact James Sutherland, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6533; fax: 425–917– 6590; email: james.sutherland@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Special Attention Service Bulletin 777–32–0083, Revision 1, dated February 17, 2011. (3) 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; Internet https:// www.myboeingfleet.com. (4) 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. (5) 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 June 7, 2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–14544 Filed 6–22–12; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\25JNR1.SGM 25JNR1

Agencies

[Federal Register Volume 77, Number 122 (Monday, June 25, 2012)]
[Rules and Regulations]
[Pages 37781-37783]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-14544]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1412; Directorate Identifier 2011-NM-158-AD; 
Amendment 39-17088; AD 2012-12-08]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 777-200 and -300 series airplanes. This AD was 
prompted by reports of cracked retract actuator fuse pins that can fail 
earlier than the previously determined safe life limit of the pins. A 
fractured retract actuator fuse pin can cause the main landing gear to 
extend without restriction and attempt to lock into position under high 
dynamic loads. This AD requires an inspection for the part number of 
the fuse pin, and replacement of the pin if necessary. We are issuing 
this AD to prevent structural damage to the side and drag brace lock 
assemblies, which could result in landing gear collapse during 
touchdown, rollout, or taxi.

DATES: This AD is effective July 30, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of July 30, 
2012.

ADDRESSES: 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; 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 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

[[Page 37782]]

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: James Sutherland, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6533; fax: 
425-917-6590; email: james.sutherland@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 published in the Federal Register on December 30, 2011 (76 FR 
82210). That NPRM proposed to require an inspection for the part number 
of the fuse pin, and replacement of the pin if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(76 FR 82210, December 30, 2011) and the FAA's response to each 
comment.

Request To Revise the Compliance Time and Include Revised Service 
Information

    Boeing and United Airlines requested that we revise the NPRM (76 FR 
82210, December 30, 2011) to refer to Boeing Special Attention Service 
Bulletin 777-32-0083, Revision 2 (not yet released). Boeing stated that 
it had performed a new risk-based assessment and found that 18 months 
is adequate to mitigate the remaining fleet risk. Boeing requested the 
compliance time be changed to 18 months from the date of the service 
bulletin. Also, Boeing requested that we provide credit for actions 
accomplished in accordance with Boeing Special Attention Service 
Bulletin 777-32-0083, Revision 1, dated February 17, 2011.
    We partially agree. We agree to update the compliance time to 18 
months based on the new risk-based safety assessment. We revised 
paragraphs (g), (g)(2), and (g)(3) of this AD to reflect an initial 
compliance time of 18 months. We disagree with delaying issuance of the 
final rule to reference Boeing Special Attention Service Bulletin 777-
32-0083, Revision 2, because that service information is not published 
at this time. Operators may request approval of an alternative method 
of compliance (AMOC) once Revision 2 of Boeing Special Attention 
Service Bulletin 777-32-0083 is released.

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 82210, December 30, 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 82210, December 30, 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 proposed AD affects 35 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                 Action                          Labor cost           Parts cost      product       operators
----------------------------------------------------------------------------------------------------------------
Inspection.............................  4 work-hours x $85 per               $0          $340          $11,900
                                          hour = $340.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary pin 
replacements that would be required based on the results of the 
inspection. We have no way of determining the number of aircraft that 
might need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                        Labor cost               Parts cost            Cost per  product
----------------------------------------------------------------------------------------------------------------
Pin replacement.....................  1 work-hour x $85 per    $769 per pin...........  $854 per pin.
                                       hour = $85 per pin.
----------------------------------------------------------------------------------------------------------------

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 the DOT Regulatory Policies 
and

[[Page 37783]]

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):

2012-12-08 The Boeing Company: Amendment 39-17088; Docket No. FAA-
2011-1412; Directorate Identifier 2011-NM-158-AD.

(a) Effective Date

    This AD is effective July 30, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 777-200 and -S300 
series airplanes; certificated in any category; as identified in 
Boeing Special Attention Service Bulletin 777-32-0083, Revision 1, 
dated February 17, 2011.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 32: Main landing gear.

(e) Unsafe Condition

    This AD was prompted by reports of cracked retract actuator fuse 
pins that can fail earlier than the previously determined safe life 
limit of the pins. A fractured retract actuator fuse pin can cause 
the main landing gear (MLG) to extend without restriction and 
attempt to lock into position under high dynamic loads. We are 
issuing this AD to prevent structural damage to the side and drag 
brace lock assemblies, which could result in landing gear collapse 
during touchdown, rollout, or taxi.

(f) Compliance

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

(g) Inspection of Retract Actuator Fuse Pin

    Within 18 months after the effective date of this AD: Inspect 
the part number of the fuse pins of the left and right MLG retract 
actuators, in accordance with the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 777-32-0083, Revision 1, 
dated February 17, 2011. A review of airplane maintenance records is 
acceptable in lieu of this inspection if the part number of the 
installed actuator fuse pin can be conclusively determined from that 
review.
    (1) If any retract actuator fuse pin having part number 
112W1769-3 is found installed, no further action is required by this 
paragraph for that fuse pin.
    (2) If any retract actuator fuse pin having part number 
112W1769-1 is found installed and the pin has accumulated more than 
10,000 total flight cycles as of the effective date of this AD: 
Within 18 months after the effective date of this AD, replace the 
fuse pin with a new part number 112W1769-3 fuse pin, in accordance 
with the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 777-32-0083, Revision 1, dated February 17, 2011.
    (3) If any retract actuator fuse pin having part number 
112W1769-1 is found installed and the pin has accumulated 8,000 or 
more total flight cycles, but fewer than or equal to 10,000 total 
flight cycles, as of the effective date of this AD: Before the 
accumulation of 10,000 total flight cycles on the pin, or within 18 
months after the effective date of this AD, whichever occurs later, 
replace the fuse pin with a new part number 112W1769-3 fuse pin, in 
accordance with the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 777-32-0083, Revision 1, dated February 
17, 2011.
    (4) If any retract actuator fuse pin having part number 
112W1769-1 is found installed and the pin has accumulated fewer than 
8,000 total flight cycles as of the effective date of this AD: 
Before the accumulation of 8,000 total flight cycles on the pin, or 
within 24 months after the effective date of this AD, whichever 
occurs later, replace the fuse pin with a new part number 112W1769-3 
fuse pin, in accordance with the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 777-32-0083, Revision 1, 
dated February 17, 2011.

(h) Parts Installation

    As of the effective date of this AD, no person may install a 
retract actuator fuse pin having part number 112W1769-1 on any 
airplane.

(i) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g) of this AD, if those actions were performed before the effective 
date of this AD using Boeing Special Attention Service Bulletin 777-
32-0083, dated February 5, 2009.

(j) 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.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by Boeing 
Commercial Airplanes Organization Designation Authorization (ODA) 
that has been authorized by the Manager, Seattle ACO, to make those 
findings. For a repair method to be approved, the repair must meet 
the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(k) Related Information

    For more information about this AD, contact James Sutherland, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6533; fax: 425-917-6590; email: 
james.sutherland@faa.gov.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the following service 
information under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Special Attention Service Bulletin 777-32-0083, 
Revision 1, dated February 17, 2011.
    (3) 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; Internet https://www.myboeingfleet.com.
    (4) 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.
    (5) 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 June 7, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-14544 Filed 6-22-12; 8:45 am]
BILLING CODE 4910-13-P